diff --git a/.gitignore b/.gitignore index 8dce03d4..d74c5136 100644 --- a/.gitignore +++ b/.gitignore @@ -7,7 +7,7 @@ new* *vtk* *.sum *.ech -*2.dat +*.dat *.docx *COMPILED* *.out diff --git a/Project.toml b/Project.toml index d0e92815..5c021409 100644 --- a/Project.toml +++ b/Project.toml @@ -1,7 +1,7 @@ name = "OWENS" uuid = "51d15398-4eaf-40f9-a029-79ae1c4a3867" authors = ["Kevin R. Moore and contributors"] -version = "1.0.2" +version = "1.0.3" [deps] Composites = "d0d699f6-c662-11e8-0fb1-1b30104ab829" diff --git a/README.md b/README.md index e9f60bac..fbab4fe5 100644 --- a/README.md +++ b/README.md @@ -3,15 +3,62 @@ [![](https://img.shields.io/badge/docs-stable-blue.svg)](https://sandialabs.github.io/OWENS.jl) ![](https://github.com/sandialabs/OWENS.jl/workflows/CI/badge.svg) -This repository is based on the original structural dynamics solver by Brian Owens (see dissertation: http://hdl.handle.net/1969.1/151813). -The original code has been translated to Julia and revised for simplicity and performance while maintaining accuracy. GXBeam.jl has also been coupled for geometrically exact beam solutions -The aerodynamics are provided by the OWENSAero.jl module (https://gitlab.sandia.gov/8821-vawt-tools/OWENSAero.jl) in addition to a coupling to the OpenFAST AeroDyn module. All codes that can be standalone (like the aerodynamics and structures) should be separate and handled through the dependency manager, other functions specific to the OWENS ontology should remain in this repository. -## Examples -Please see the documentation under examples. +This package was based on the original structural dynamics solver by Brian Owens (see dissertation: http://hdl.handle.net/1969.1/151813). However, it has been rewritten into the Julia programming language and many of the issues related to aerodynamic coupling and floating dynamics solved, with extensive expansion into other areas and features to provide a seamless and automated process that takes in high level design details and does all of the preprocessing, running, and post processing that is normally done under different roofs or by different manual processes. This was done with the intent of enabling fast, parametric design. We have many of the modules propogating automatic gradients, however this is still a future challenge to solve well. -## Installation -Please see the documentation under setup. +This package is for experienced researchers with both software and engineering experience who need generalized flexibility and performance that is 100% open source. If you want a windows compatible GUI, please use QBlade from our friends across the pond. -## Contributing -Please make all feature changes and bug fixes as branches and then create pull requests against the dev branch. The dev branch will be periodically pulled into master for significant version changes. +Here are several examples of OWENS use cases, current and past, including the Sandia 34m research turbine. + +drawing + +Then here is an example of a helical design. Note that arbitrary numbers of struts can be specified in the automatic meshing functions. You can also write your own generalized mesh using the internal building blocks, but it is not thouroughly documented. + +drawing + +The generalized meshing was modified to include HAWT concepts, like this bi-wing concept. OWENS is capable of axial flow turbines/HAWTs, but it is not a mature feature, and no where near as developed as OpenFAST (i.e. for regular HAWTs it is recommended to use that software). + +drawing + +Then, floating turbines are a possibility, though this feature adds another dimension to the nonlinear time stepping convergance and in turn a fair amount of time. Future work is to make this general interface and functionality an easy to use feature (right now it needs a high level of experience to use). + +drawing + + +# OWENS under the hood + +The OWENS.jl package contains functions and interfaces related to the ontology (how everything comes together, forms a wind turbine, and operates like a wind turbine), with preprocessing and postprocessing helper functions. These include automated meshing functions, sectional property mapping, two-way loads mapping, generalized torque and direct mesh controls, algorithms for two-way coupling and time stepping, fatigue and design equivalent load calculation, and all of the ontology and coupling to the other packages used. + +OWENSPrecomp.jl is a translation of Precomp and calculates the sectional properties + +Composites.jl provides classical laminate theory definitions used for both pre and post processing + +OWENSFEA.jl is one of the structural models including a Timoshenko beam solver in the linear and nonlinear steady, modal, time domain, and reduced order modal domains. + +GXBeam.jl has also been integrated for geometrically exact beam solutions of the same above + +The aerodynamics are provided by the OWENSAero.jl module, or optionally OpenFAST OLAF via OWENSOpenFASTWrappers.jl + +Floating dynamics are provided by OWENSOpenFASTWrappers.jl and the HydroDyn and MoorDyn libraries + +Turbulent inflow is provided by OWENSOpenFASTWrappers.jl and the inflowwind and turbsim libraries + +Rainflow counting was provided by Rainflow.jl, however, this package became orphained and was pulled into the OWENS code base. + +## Installation +Please follow the instructions on the setup page + +## Documentation +- https://sandialabs.github.io/OWENS.jl +- All of the functions have docstrings describing the i/o and function purpose, which can be accessed the docs site or by: + * import module + * ? module.function() +- A note about julia debuggers – if you don’t want it to step through everything, you need to tell it what packages to compile vs while packages to step through. This will make the debugger comparable (if not faster) than Matlab in speed. In VSCode, this can be done in the debug pane. + +## Software License + +Copyright 2021 National Technology & Engineering Solutions of Sandia, LLC (NTESS). +Under the terms of Contract DE-NA0003525 with NTESS, there is a non-exclusive license for use of this work by or on behalf of the U.S. Government. +Export of this data may require a license from the United States Government. + +See Copyright.txt file for more information diff --git a/docs/src/OWENS_Dev_Guide.md b/docs/src/OWENS_Dev_Guide.md index 5eb1a4e6..1242918a 100644 --- a/docs/src/OWENS_Dev_Guide.md +++ b/docs/src/OWENS_Dev_Guide.md @@ -112,6 +112,12 @@ though it were a north starting blade rotating clockwise, and a symmetric gust velocity will match (if the simple iec uniform gust is used). All else for CACTUS follows the description above. +Aerodynamics forces are radial inward positive and tangential in direction of rotation positive. +So, the blade local accelerations in the radial will be outward positive and in the tangential +will be in the opposite direction of rotation for a CCW rotor. CW rotors are still in work and +would need to have the local frame of reference rotation verified. Therefor, for the added mass + equations, the forces should be negated. + ## OWENSFEA Structures Yaw is equivalent to the global azimuth angle as above, and is denoted diff --git a/docs/src/assets/SNL34m.png b/docs/src/assets/SNL34m.png new file mode 100644 index 00000000..3774d003 Binary files /dev/null and b/docs/src/assets/SNL34m.png differ diff --git a/docs/src/assets/arcus.png b/docs/src/assets/arcus.png new file mode 100644 index 00000000..4aad5535 Binary files /dev/null and b/docs/src/assets/arcus.png differ diff --git a/docs/src/assets/biwing.png b/docs/src/assets/biwing.png new file mode 100644 index 00000000..9729f38b Binary files /dev/null and b/docs/src/assets/biwing.png differ diff --git a/docs/src/assets/helical.png b/docs/src/assets/helical.png new file mode 100644 index 00000000..6e3db3f7 Binary files /dev/null and b/docs/src/assets/helical.png differ diff --git a/docs/src/getting_started.md b/docs/src/getting_started.md new file mode 100644 index 00000000..8aa44af1 --- /dev/null +++ b/docs/src/getting_started.md @@ -0,0 +1,7 @@ +# Optimization Considerations + +My text + +[comment] ![](../assets/OWENS_Example_Figure_Building_Blocks.png) + +my text \ No newline at end of file diff --git a/docs/src/index.md b/docs/src/index.md index b2d89bbf..e9bb81d2 100644 --- a/docs/src/index.md +++ b/docs/src/index.md @@ -1,14 +1,52 @@ -# OWENS (Offshore Wind ENergy Simulator) +# OWENS (Onshore/Offshore Wind/Water ENergy Simulator) -This repository is based on the original structural dynamics solver by Brian Owens (see dissertation: http://hdl.handle.net/1969.1/151813). -The original code has been translated to Julia and revised for simplicity and performance while maintaining accuracy. GXBeam.jl has also been integrated in beta form for geometrically exact beam solutions -The aerodynamics are provided by the OWENSAero.jl module (https://gitlab.sandia.gov/8821-vawt-tools/OWENSAero.jl) in addition to a coupling to the OpenFAST AeroDyn module. +This package was based on the original structural dynamics solver by Brian Owens (see dissertation: http://hdl.handle.net/1969.1/151813). However, it has been rewritten into the Julia programming language and many of the issues related to aerodynamic coupling and floating dynamics solved, with extensive expansion into other areas and features to provide a seamless and automated process that takes in high level design details and does all of the preprocessing, running, and post processing that is normally done under different roofs or by different manual processes. This was done with the intent of enabling fast, parametric design. We have many of the modules propogating automatic gradients, however this is still a future challenge to solve well. -## Documentation +This package is for experienced researchers with both software and engineering experience who need generalized flexibility and performance that is 100% open source. If you want a windows compatible GUI, please use QBlade from our friends across the pond. + +Here are several examples of OWENS use cases, current and past, including the Sandia 34m research turbine. + +drawing + +Then here is an example of a helical design. Note that arbitrary numbers of struts can be specified in the automatic meshing functions. You can also write your own generalized mesh using the internal building blocks, but it is not thouroughly documented. + +drawing + +The generalized meshing was modified to include HAWT concepts, like this bi-wing concept. OWENS is capable of axial flow turbines/HAWTs, but it is not a mature feature, and no where near as developed as OpenFAST (i.e. for regular HAWTs it is recommended to use that software). + +drawing + +Then, floating turbines are a possibility, though this feature adds another dimension to the nonlinear time stepping convergance and in turn a fair amount of time. Future work is to make this general interface and functionality an easy to use feature (right now it needs a high level of experience to use). + +drawing + + +# OWENS under the hood -In Work: Documentation can be found in the docs folder along with the validation paper(s). +The OWENS.jl package contains functions and interfaces related to the ontology (how everything comes together, forms a wind turbine, and operates like a wind turbine), with preprocessing and postprocessing helper functions. These include automated meshing functions, sectional property mapping, two-way loads mapping, generalized torque and direct mesh controls, algorithms for two-way coupling and time stepping, fatigue and design equivalent load calculation, and all of the ontology and coupling to the other packages used. + +OWENSPrecomp.jl is a translation of Precomp and calculates the sectional properties + +Composites.jl provides classical laminate theory definitions used for both pre and post processing + +OWENSFEA.jl is one of the structural models including a Timoshenko beam solver in the linear and nonlinear steady, modal, time domain, and reduced order modal domains. + +GXBeam.jl has also been integrated for geometrically exact beam solutions of the same above + +The aerodynamics are provided by the OWENSAero.jl module, or optionally OpenFAST OLAF via OWENSOpenFASTWrappers.jl + +Floating dynamics are provided by OWENSOpenFASTWrappers.jl and the HydroDyn and MoorDyn libraries + +Turbulent inflow is provided by OWENSOpenFASTWrappers.jl and the inflowwind and turbsim libraries + +Rainflow counting was provided by Rainflow.jl, however, this package became orphained and was pulled into the OWENS code base. + +## Installation +Please follow the instructions on the setup page + +## Documentation -- All of the functions have docstrings describing the i/o and function purpose, which can be accessed by: +- All of the functions have docstrings describing the i/o and function purpose, which can be accessed the docs site or by: * import module * ? module.function() - A note about julia debuggers – if you don’t want it to step through everything, you need to tell it what packages to compile vs while packages to step through. This will make the debugger comparable (if not faster) than Matlab in speed. In VSCode, this can be done in the debug pane. diff --git a/docs/src/literate/B_detailedInputs.jl b/docs/src/literate/B_detailedInputs.jl index 95cc7453..2da08541 100644 --- a/docs/src/literate/B_detailedInputs.jl +++ b/docs/src/literate/B_detailedInputs.jl @@ -110,7 +110,7 @@ mass_breakout_blds,mass_breakout_twr,system,assembly,sections,AD15bldNdIdxRng, A NuMad_mat_xlscsv_file_bld,# = "$path/data/NuMAD_Materials_SNL_5MW_D_Carbon_LCDT_ThickFoils_ThinSkin.csv", NuMad_geom_xlscsv_file_strut, NuMad_mat_xlscsv_file_strut, - Ht=towerHeight, + Htwr_base=towerHeight, ntelem, nbelem, ncelem, diff --git a/docs/src/literate/C_customizablePreprocessing.jl b/docs/src/literate/C_customizablePreprocessing.jl index 9761f949..36cae866 100644 --- a/docs/src/literate/C_customizablePreprocessing.jl +++ b/docs/src/literate/C_customizablePreprocessing.jl @@ -87,9 +87,9 @@ stack_layers_bld = nothing stack_layers_scale = [1.0,1.0] chord_scale = [1.0,1.0] thickness_scale = [1.0,1.0] -Ht=towerHeight +Htwr_base=towerHeight strut_mountpointbot = 0.11 -strut_mountpointtop = 0.11 +strut_mountpointtop = 0.89 joint_type = 0 c_mount_ratio = 0.05 angularOffset = -pi/2 @@ -126,8 +126,8 @@ nothing ### Set up mesh ######################################### if meshtype == "ARCUS" #TODO, for all of these propogate the AeroDyn additional output requirements - mymesh,myort,myjoint = OWENS.create_arcus_mesh(;Ht, - Hb = H, #blade height + mymesh,myort,myjoint = OWENS.create_arcus_mesh(;Htwr_base, + Hbld = H, #blade height R, # m bade radius nblade = Nbld, ntelem, #tower elements @@ -147,18 +147,16 @@ elseif meshtype == "Darrieus" || meshtype == "H-VAWT" connectBldTips2Twr = false end - mymesh, myort, myjoint, AD15bldNdIdxRng, AD15bldElIdxRng = OWENS.create_mesh_struts(;Ht, - Hb = H, #blade height + mymesh, myort, myjoint, AD15bldNdIdxRng, AD15bldElIdxRng = OWENS.create_mesh_struts(;Htwr_base, + Hbld = H, #blade height R, # m bade radius AD15hubR=2.0, nblade = Nbld, ntelem, #tower elements nbelem, #blade elements nselem, - strut_twr_mountpointbot = strut_mountpointbot, # This puts struts at top and bottom - strut_twr_mountpointtop = strut_mountpointtop, # This puts struts at top and bottom - strut_bld_mountpointbot = strut_mountpointbot, # This puts struts at top and bottom - strut_bld_mountpointtop = strut_mountpointtop, # This puts struts at top and bottom + strut_twr_mountpoint = [strut_mountpointbot,strut_mountpointtop], # This puts struts at top and bottom + strut_bld_mountpoint = [strut_mountpointbot,strut_mountpointtop], # This puts struts at top and bottom bshapex = shapeX, #Blade shape, magnitude is irrelevant, scaled based on height and radius above bshapez = shapeZ, bshapey = zeros(nbelem+1), # but magnitude for this is relevant @@ -526,7 +524,7 @@ if AD15On OWENSOpenFASTWrappers.writeIWfile(Vinf,ifw_input_file;windINPfilename) - OWENSOpenFASTWrappers.setupTurb(adi_lib,ad_input_file,ifw_input_file,adi_rootname,[shapeX],[shapeZ],[B],[Ht],[mymesh],[myort],[AD15bldNdIdxRng],[AD15bldElIdxRng]; + OWENSOpenFASTWrappers.setupTurb(adi_lib,ad_input_file,ifw_input_file,adi_rootname,[shapeX],[shapeZ],[B],[Htwr_base],[mymesh],[myort],[AD15bldNdIdxRng],[AD15bldElIdxRng]; rho = rho, adi_dt = delta_t, adi_tmax= numTS*delta_t, @@ -552,7 +550,7 @@ nothing # Calculate mass breakout of each material mass_breakout_bld = OWENS.get_material_mass(plyprops_bld,numadIn_bld) mass_breakout_blds = mass_breakout_bld.*length(mymesh.structuralNodeNumbers[:,1]) -mass_breakout_twr = OWENS.get_material_mass(plyprops_twr,numadIn_twr;int_start=0.0,int_stop=Ht) +mass_breakout_twr = OWENS.get_material_mass(plyprops_twr,numadIn_twr;int_start=0.0,int_stop=Htwr_base) ################################ ##### End setupOWENS diff --git a/docs/src/setup.md b/docs/src/setup.md index 22cf0e0d..4c286a55 100644 --- a/docs/src/setup.md +++ b/docs/src/setup.md @@ -335,7 +335,7 @@ If you get an error about attempting to access library xyz, but it doesn't exist adi_lib = "path/to/openfast/build/modules/libraryfolder/libraryname" ``` - cd OWENS.jl/test + cd OWENS.jl/examples/SNL34m julia SNL34mVAWTNormalOperation.jl You can visualize the output vtk/vtu/pvd paraview files with paraview, install paraview via diff --git a/examples/dev/WINDIO_example.yaml b/examples/Optimization/WINDIO_example.yaml similarity index 100% rename from examples/dev/WINDIO_example.yaml rename to examples/Optimization/WINDIO_example.yaml diff --git a/examples/Optimization/WINDIO_opt_start.yaml b/examples/Optimization/WINDIO_opt_start.yaml new file mode 100644 index 00000000..d5ec5fe8 --- /dev/null +++ b/examples/Optimization/WINDIO_opt_start.yaml @@ -0,0 +1,1063 @@ +name: WINDIO Example +assembly: {turbine_class: I, turbulence_class: B, drivetrain: geared, rotor_orientation: upwind, number_of_blades: 3, hub_height: -25.2, rotor_diameter: 20.0, rated_power: 500000, lifetime: 25.0, marine_hydro: true} +components: + blade: + outer_shape_bem: + airfoil_position: + grid: &id001 [0.0, 0.016666666666666666, 0.05, 0.08333333333333333, 0.11666666666666667, 0.15000000000000002, 0.18333333333333332, 0.21666666666666667, 0.25, 0.2833333333333333, 0.31666666666666665, 0.35, 0.38333333333333336, 0.4166666666666667, 0.44999999999999996, 0.4833333333333333, 0.5166666666666667, 0.55, 0.5833333333333334, 0.6166666666666667, 0.6499999999999999, 0.6833333333333333, 0.7166666666666667, 0.75, 0.7833333333333333, 0.8166666666666667, 0.8500000000000001, 0.8833333333333333, 0.9166666666666666, 0.9500000000000001, 0.9833333333333333, 1.0] + labels: [NACA6_1000, NACA6_1000, NACA6_0864, NACA6_0629, NACA6_0444, NACA6_0329, NACA6_0276, NACA6_0259, NACA6_0247, NACA6_0240, NACA6_0240, NACA6_0240, NACA6_0240, NACA6_0240, NACA6_0240, NACA6_0240, NACA6_0240, NACA6_0240, NACA6_0240, NACA6_0240, NACA6_0240, NACA6_0240, NACA6_0240, NACA6_0240, NACA6_0240, NACA6_0240, NACA6_0240, NACA6_0240, NACA6_0240, NACA6_0240, NACA6_0240, NACA6_0240] + chord: + grid: *id001 + values: [0.8, 0.8, 0.894, 1.118, 1.386, 1.61, 1.704, 1.662, 1.619, 1.577, 1.534, 1.492, 1.45, 1.407, 1.365, 1.322, 1.279, 1.235, 1.192, 1.148, 1.103, 1.058, 1.012, 0.966, 0.92, 0.872, 0.824, 0.776, 0.726, 0.676, 0.626, 0.626] + twist: + grid: *id001 + values: [0.22444934180647075, 0.22444934180647075, 0.22444934180647075, 0.22444934180647075, 0.22444934180647075, 0.22444934180647075, 0.22444934180647075, 0.20141099568014562, 0.182212373908208, 0.1658062789394613, 0.1520181778487061, 0.13997540600994524, 0.12967796342317867, 0.12060225131280816, 0.11257373675363426, 0.1054178868204575, 0.09913470151327791, 0.09337511498169662, 0.08813912722571364, 0.08325220532012952, 0.07871434926494426, 0.07435102613495843, 0.07033676885537149, 0.06632251157578452, 0.06230825429619756, 0.058468529941810045, 0.05462880558742251, 0.05061454830783556, 0.0466002910282486, 0.042411500823462206, 0.03804817769347638, 0.03804817769347638] + pitch_axis: + grid: *id001 + values: [0.5, 0.49071825396825397, 0.459, 0.4099472222222222, 0.3611440476190476, 0.3294, 0.32, 0.32, 0.32, 0.32, 0.32, 0.32, 0.32, 0.32, 0.32, 0.32, 0.32, 0.32, 0.32, 0.32, 0.32, 0.32, 0.32, 0.32, 0.32, 0.32, 0.32, 0.32, 0.32, 0.32, 0.32, 0.32] + reference_axis: + x: + grid: *id001 + values: [-0.0, -0.0, -0.0, -0.0, -0.0, -0.0, -0.0, -0.0, -0.0, -0.0, -0.0, -0.0, -0.0, -0.0, -0.0, -0.0, -0.0, -0.0, -0.0, -0.0, -0.0, -0.0, -0.0, -0.0, -0.0, -0.0, -0.0, -0.0, -0.0, -0.0, -0.0, -0.0] + y: + grid: *id001 + values: [0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0] + z: + grid: *id001 + values: [0.0, 0.15, 0.45, 0.75, 1.05, 1.35, 1.65, 1.95, 2.25, 2.55, 2.85, 3.15, 3.45, 3.75, 4.05, 4.35, 4.65, 4.95, 5.25, 5.55, 5.85, 6.15, 6.45, 6.75, 7.05, 7.35, 7.65, 7.95, 8.25, 8.55, 8.85, 9.0] + internal_structure_2d_fem: + reference_axis: + 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0.20710219005339656, 0.22613625340452875, 0.24517031675566095, 0.2660887252285566, 0.2870071337014522, 0.30792554217434787, 0.3288439506472435, 0.350911029806978, 0.3729781089667125, 0.39504518812644707, 0.41711226728618156, 0.4391793464459161, 0.45887775857841995, 0.47857617071092373, 0.49827458284342757, 0.5179729949759314, 0.5376714071084352, 0.5577786570700229, 0.5778859070316106, 0.5979931569931983, 0.618100406954786, 0.6382076569163737, 0.657284256252832, 0.6763608555892903, 0.6954374549257486, 0.7145140542622068, 0.7335906535986652, 0.7526672529351234, 0.7717438522715817, 0.8, 0.8187500000000001, 0.8375, 0.85625, 0.875, 0.89375, 0.9125, 0.9312499999999999, 0.95] + values: [0.043, 0.04188235294117647, 0.04076470588235294, 0.039913771285478794, 0.03906283668860465, 0.038211902091730504, 0.03736096749485635, 0.0365100328979822, 0.03557485698978217, 0.034639681081582135, 0.03370450517338209, 0.03276932926518204, 0.031782801020393915, 0.03079627277560579, 0.029809744530817663, 0.02882321628602953, 0.027836688041241398, 0.026956053145905937, 0.02607541825057048, 0.025194783355235006, 0.024314148459899543, 0.02343351356456408, 0.022534601213340156, 0.021635688862116233, 0.020736776510892303, 0.019837864159668383, 0.01893895180844446, 0.01808611560281456, 0.017233279397184664, 0.016380443191554763, 0.015527606985924867, 0.014674770780294964, 0.013821934574665068, 0.012969098369035169, 0.011705882352941174, 0.010867647058823525, 0.01002941176470588, 0.009191176470588236, 0.008352941176470586, 0.0075147058823529355, 0.006676470588235292, 0.005838235294117648, 0.005000000000000001] + fiber_orientation: + values: [0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0] + grid: [0.1, 0.125, 0.15, 0.1690340633511322, 0.18806812670226436, 0.20710219005339656, 0.22613625340452875, 0.24517031675566095, 0.2660887252285566, 0.2870071337014522, 0.30792554217434787, 0.3288439506472435, 0.350911029806978, 0.3729781089667125, 0.39504518812644707, 0.41711226728618156, 0.4391793464459161, 0.45887775857841995, 0.47857617071092373, 0.49827458284342757, 0.5179729949759314, 0.5376714071084352, 0.5577786570700229, 0.5778859070316106, 0.5979931569931983, 0.618100406954786, 0.6382076569163737, 0.657284256252832, 0.6763608555892903, 0.6954374549257486, 0.7145140542622068, 0.7335906535986652, 0.7526672529351234, 0.7717438522715817, 0.8, 0.8187500000000001, 0.8375, 0.85625, 0.875, 0.89375, 0.9125, 0.9312499999999999, 0.95] + - name: web1_skinTE + material: glass_biax + web: web1 + thickness: + grid: [0.1, 0.125, 0.15, 0.1690340633511322, 0.18806812670226436, 0.20710219005339656, 0.22613625340452875, 0.24517031675566095, 0.2660887252285566, 0.2870071337014522, 0.30792554217434787, 0.3288439506472435, 0.350911029806978, 0.3729781089667125, 0.39504518812644707, 0.41711226728618156, 0.4391793464459161, 0.45887775857841995, 0.47857617071092373, 0.49827458284342757, 0.5179729949759314, 0.5376714071084352, 0.5577786570700229, 0.5778859070316106, 0.5979931569931983, 0.618100406954786, 0.6382076569163737, 0.657284256252832, 0.6763608555892903, 0.6954374549257486, 0.7145140542622068, 0.7335906535986652, 0.7526672529351234, 0.7717438522715817, 0.8, 0.8187500000000001, 0.8375, 0.85625, 0.875, 0.89375, 0.9125, 0.9312499999999999, 0.95] + values: [0.002, 0.001955882352941177, 0.0019117647058823533, 0.0018781751823215315, 0.0018445856587607098, 0.001810996135199888, 0.0017774066116390667, 0.0017438170880782456, 0.0017069022495966651, 0.0016699874111150846, 0.0016330725726335042, 0.0015961577341519235, 0.0015572158297523914, 0.0015182739253528598, 0.0014793320209533286, 0.0014403901165537974, 0.0014014482121542657, 0.0013666863083910236, 0.0013319244046277818, 0.0012971625008645394, 0.0012624005971012973, 0.0012276386933380555, 0.0011921553110529005, 0.0011566719287677458, 0.001121188546482591, 0.0010857051641974364, 0.0010502217819122813, 0.0010165571948479433, 0.000982892607783605, 0.0009492280207192671, 0.000915563433654929, 0.0008818988465905908, 0.0008482342595262528, 0.0008145696724619145, 0.0007647058823529412, 0.0007316176470588235, 0.0006985294117647059, 0.0006654411764705883, 0.0006323529411764706, 0.0005992647058823529, 0.0005661764705882353, 0.0005330882352941178, 0.0005000000000000001] + fiber_orientation: + values: [0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0] + grid: [0.1, 0.125, 0.15, 0.1690340633511322, 0.18806812670226436, 0.20710219005339656, 0.22613625340452875, 0.24517031675566095, 0.2660887252285566, 0.2870071337014522, 0.30792554217434787, 0.3288439506472435, 0.350911029806978, 0.3729781089667125, 0.39504518812644707, 0.41711226728618156, 0.4391793464459161, 0.45887775857841995, 0.47857617071092373, 0.49827458284342757, 0.5179729949759314, 0.5376714071084352, 0.5577786570700229, 0.5778859070316106, 0.5979931569931983, 0.618100406954786, 0.6382076569163737, 0.657284256252832, 0.6763608555892903, 0.6954374549257486, 0.7145140542622068, 0.7335906535986652, 0.7526672529351234, 0.7717438522715817, 0.8, 0.8187500000000001, 0.8375, 0.85625, 0.875, 0.89375, 0.9125, 0.9312499999999999, 0.95] + root: {d_f: 0.03, sigma_max: 675000000.0} + joint: {position: 0.0, mass: 0.0, cost: 0.0, bolt: M30, nonmaterial_cost: 0.0, reinforcement_layer_ss: joint_reinf_ss, reinforcement_layer_ps: joint_reinf_ps} + hub: {diameter: 2.0, cone_angle: 0.0, drag_coefficient: 0.0, flange_t2shell_t: 6.0, flange_OD2hub_D: 0.6, flange_ID2OD: 0.8, hub_blade_spacing_margin: 1.2, hub_stress_concentration: 3.0, n_front_brackets: 5, n_rear_brackets: 5, clearance_hub_spinner: 0.5, spin_hole_incr: 1.2, pitch_system_scaling_factor: 0.75, spinner_gust_ws: 70.0, hub_material: cast_iron, spinner_material: glass_uni} + nacelle: + drivetrain: + uptilt: -0.0 + distance_tt_hub: 1.2 + distance_hub_mb: 2.0 + distance_mb_mb: 1.0 + overhang: 4.91 + generator_length: 2.0 + generator_radius_user: 0.25 + generator_mass_user: 8928.0 + generator_rpm_efficiency_user: + grid: [0.0,1.0] + values: [1.0,1.0] + gear_ratio: 53.0 + gearbox_length_user: 0.0 + gearbox_radius_user: 0.0 + gearbox_mass_user: 0.0 + gearbox_efficiency: 0.92 + damping_ratio: 0.01 + lss_diameter: [0.577, 0.577] + lss_wall_thickness: [0.288, 0.288] + lss_material: steel + hss_length: 1.5 + hss_diameter: [0.288, 0.288] + hss_wall_thickness: [0.144, 0.144] + hss_material: steel + nose_diameter: [0.3, 0.3] + nose_wall_thickness: [0.1, 0.1] + bedplate_wall_thickness: + grid: [0.0, 1.0] + values: [0.05, 0.05] + bedplate_flange_width: 1.0 + bedplate_flange_thickness: 0.05 + bedplate_web_thickness: 0.05 + bedplate_material: steel + mb1Type: CARB + mb2Type: SRB + uptower: true + gear_configuration: eep + planet_numbers: [3, 3, 0] + brake_mass_user: 0.0 + hvac_mass_coefficient: 0.025 + converter_mass_user: 0.0 + transformer_mass_user: 0.0 + # generator: {generator_type: DFIG, rho_Fe: 7700.0, rho_Fes: 7850.0, rho_Copper: 8900.0, rho_PM: 7450.0, B_r: 1.2, P_Fe0e: 1.0, P_Fe0h: 4.0, S_N: -0.002, alpha_p: 1.0995574287564276, b_r_tau_r: 0.45, b_ro: 0.004, b_s_tau_s: 0.45, b_so: 0.004, freq: 60, h_i: 0.001, h_sy0: 0.0, h_w: 0.005, k_fes: 0.9, k_s: 0.2, m: 3, mu_0: 1.2566370614359173e-06, mu_r: 1.06, p: 3.0, phi: 1.5707963267948966, ratio_mw2pp: 0.7, resist_Cu: 2.52e-08, y_tau_pr: 0.8333333, rated_rpm: 1200.0, cofi: 0.9, y_tau_p: 0.8, sigma: 21500.0, rad_ag: 0.61, len_s: 0.49, h_s: 0.08, I_0: 40.0, B_symax: 1.3, S_Nmax: -0.2, h_0: 0.01, k_fillr: 0.55, k_fills: 0.65, q1: 5, q2: 4, C_Cu: 4.786, C_Fe: 0.556, C_Fes: 0.50139, C_PM: 50.0, mass_coefficient: 0.0, q3: 4, d_r: 0.0, h_m: 0.0, n_r: 0.0, t_wr: 0.0, n_s: 0.0, b_st: 0.0, d_s: 0.0, t_ws: 0.0} + tower: + outer_shape_bem: + reference_axis: + x: + grid: [0.375, 0.5833333333333334, 0.7916666666666666, 1.0] + values: [0, 0, 0, 0] + y: + grid: [0.375, 0.5833333333333334, 0.7916666666666666, 1.0] + values: [0, 0, 0, 0] + z: + grid: [0.375, 0.5833333333333334, 0.7916666666666666, 1.0] + values: [-9.0, -14.0, -19.0, -24.0] + outer_diameter: + grid: [0.375, 0.5833333333333334, 0.7916666666666666, 1.0] + values: [0.3253, 0.3253, 0.3253, 0.3253] + drag_coefficient: + grid: [0.375, 0.5833333333333334, 0.7916666666666666, 1.0] + values: [0.2, 0.2, 0.2, 0.2] + internal_structure_2d_fem: + outfitting_factor: 1.07 + reference_axis: + x: + grid: [0.0, 1.0] + values: [0.0, 0.0] + y: + grid: [0.0, 1.0] + values: [0.0, 0.0] + z: + grid: [0.0, 7.728811463372998e-05, 0.10047454902385111, 0.10055183713848485, 0.20094909804770222, 0.20102638616233595, 0.30142364707155334, 0.30150093518618704, 0.40189819609540445, 0.40197548421003826, 0.5023727451192556, 0.5024500332338894, 0.6028472941431067, 0.6029245822577405, 0.7033218431669578, 0.7033991312815916, 0.8037963921908089, 0.8038736803054427, 0.90427094121466, 0.9043482293292937, 1.0] + values: [15, 15.01, 28, 28.01, 41, 41.01, 54, 54.01, 67, 67.01, 80, 80.01, 93, 93.01, 106, 106.01, 119, 119.01, 132, 132.01, 144.386] + layers: + - name: tower_wall + material: steel + thickness: + grid: [0.0, 0.10047454902385111, 0.20094909804770222, 0.30142364707155334, 0.40189819609540445, 0.5023727451192556, 0.6028472941431067, 0.7033218431669578, 0.8037963921908089, 0.90427094121466, 1.0] + values: [0.09, 0.0870568244887821, 0.06969791129654272, 0.06659467020278927, 0.048969783194233195, 0.04562355995431616, 0.028128174258004363, 0.025616868141627953, 0.009881156462835017, 0.009941082963793929, 0.005931142626464429] + floating_platform: + joints: + - name: 'downstream_upper_col' + location: [28.0, 0.0, 6.0] + cylindrical: True + axial_coeffs: &ax_coeffs_col + Cd: 0.0 + Ca: 0.0 + Cp: 0.0 + - name: 'downstream_lower_col' + location: [28.0, 0.0, -10.0] + cylindrical: True + axial_coeffs: *ax_coeffs_col + - name: 'upstream_upper_col' + location: [28.0, 3.141592653589793, 6.0] + cylindrical: True + axial_coeffs: *ax_coeffs_col + - name: 'upstream_lower_col' + location: [28.0, 3.141592653589793, -10.0] + cylindrical: True + axial_coeffs: *ax_coeffs_col + - name: 'starboard_upper_col' + location: [12, -1.5707963267948966, 6.0] + cylindrical: True + axial_coeffs: *ax_coeffs_col + - name: 'starboard_lower_col' + location: [12, -1.5707963267948966, -10.0] + cylindrical: True + axial_coeffs: *ax_coeffs_col + - name: 'port_upper_col' + location: [12, 1.5707963267948966, 6.0] + cylindrical: True + axial_coeffs: *ax_coeffs_col + - name: 'port_lower_col' + location: [12, 1.5707963267948966, -10.0] + cylindrical: True + axial_coeffs: *ax_coeffs_col + - name: upstream_heave_plate + location: [0, 0, -0.5] + relative: upstream_lower_col + axial_coeffs: &ax_coeffs_hp + Cd: 1.0 + Ca: 1.0 + Cp: 1.0 + - name: starboard_heave_plate + location: [0, 0, -0.5] + relative: starboard_lower_col + axial_coeffs: *ax_coeffs_hp + - name: downstream_heave_plate + location: [0, 0, -0.5] + relative: downstream_lower_col + axial_coeffs: *ax_coeffs_hp + - name: port_heave_plate + location: [0, 0, -0.5] + relative: port_lower_col + axial_coeffs: *ax_coeffs_hp + - name: 'anchor_1' + location: [-124.0, -50.0, -50.0] + cylindrical: false + relative: upstream_lower_col + relative_dims: [True, True, False] # z not relative + - name: 'anchor_2' + location: [-124.0, 50.0, -50.0] + cylindrical: false + relative: upstream_lower_col + relative_dims: [True, True, False] # z not relative + - name: 'anchor_3' + location: [-124.0, 0.0, -50.0] + cylindrical: false + relative: upstream_lower_col + relative_dims: [True, True, False] # z not relative + - name: 'anchor_4' + location: [124.0, -50.0, -50.0] + cylindrical: false + relative: downstream_lower_col + relative_dims: [True, True, False] # z not relative + - name: 'anchor_5' + location: [124.0, 50.0, -50.0] + cylindrical: false + relative: downstream_lower_col + relative_dims: [True, True, False] # z not relative + - name: 'anchor_6' + location: [124.0, 0.0, -50.0] + cylindrical: false + relative: downstream_lower_col + relative_dims: [True, True, False] # z not relative + + members: + - name: 'downstream_col' + joint1: 'downstream_lower_col' + joint2: 'downstream_upper_col' + outer_shape: &col_out + shape: circular + outer_diameter: + grid: [0.0, 1.0] + values: [8.0, 8.0] + internal_structure: &col_int + layers: + - name: col_twall + material: steel + thickness: + grid: [0.0, 1.0] + values: [0.02, 0.02] + ballasts: + # - variable_flag: False + # material: slurry + # volume: 40 + # grid: [0.0, 0.05] + - variable_flag: True + grid: [0.0, 0.5] + bulkhead: + material: 'steel' + thickness: + grid: [0.0, 0.5, 1.0] + values: [0.02, 0.02, 0.02] + Ca: 1.0 + Cd: 1.2 + Cp: 1.0 + axial_joints: + - {name: 'downstream_lower_pon', grid: 0.0625} + - {name: 'downstream_upper_pon', grid: 0.9375} + - name: 'upstream_col' + joint1: 'upstream_lower_col' + joint2: 'upstream_upper_col' + outer_shape: *col_out + internal_structure: *col_int + Ca: 1.0 + Cd: 1.2 + Cp: 1.0 + axial_joints: + - {name: 'upstream_lower_pon', grid: 0.0625} + - {name: 'upstream_upper_pon', grid: 0.9375} + - name: 'starboard_col' + joint1: 'starboard_lower_col' + joint2: 'starboard_upper_col' + outer_shape: *col_out + internal_structure: *col_int + Ca: 1.0 + Cd: 1.2 + Cp: 1.0 + axial_joints: + - {name: 'starboard_lower_pon', grid: 0.0625} + - {name: 'starboard_upper_pon', grid: 0.9375} + - name: 'port_col' + joint1: 'port_lower_col' + joint2: 'port_upper_col' + outer_shape: *col_out + internal_structure: *col_int + Ca: 1.0 + Cd: 1.2 + Cp: 1.0 + axial_joints: + - {name: 'port_lower_pon', grid: 0.0625} + - {name: 'port_upper_pon', grid: 0.9375} + # - name: 'downstream_heave_plate' + # joint1: 'downstream_heave_plate' + # joint2: 'downstream_lower_col' + # no_intersect: True + # outer_shape: &heave_plate_out + # shape: circular + # outer_diameter: + # grid: [0.0, 1.0] + # values: [12.0, 12.0] + # internal_structure: &heave_plate_int + # layers: + # - name: col_twall + # material: steel + # thickness: + # grid: [0.0, 1.0] + # values: [0.4, 0.4] + # Ca: 1.0 + # Cd: 1.2 + # Cp: 1.0 + # - name: 'upstream_heave_plate' + # joint1: 'upstream_heave_plate' + # joint2: 'upstream_lower_col' + # no_intersect: True + # outer_shape: *heave_plate_out + # internal_structure: *heave_plate_int + # Ca: 1.0 + # Cd: 1.2 + # Cp: 1.0 + # - name: 'port_heave_plate' + # joint1: 'port_heave_plate' + # joint2: 'port_lower_col' + # no_intersect: True + # outer_shape: *heave_plate_out + # internal_structure: *heave_plate_int + # Ca: 1.0 + # Cd: 1.2 + # Cp: 1.0 + # - name: 'starboard_heave_plate' + # joint1: 'starboard_heave_plate' + # joint2: 'starboard_lower_col' + # no_intersect: True + # outer_shape: *heave_plate_out + # internal_structure: *heave_plate_int + # Ca: 1.0 + # Cd: 1.2 + # Cp: 1.0 + - name: 'upper_pontoon_DP' + joint1: 'downstream_upper_pon' + joint2: 'port_upper_pon' + outer_shape: &pon_out + shape: circular + outer_diameter: + grid: [0.0, 1.0] + values: [2.0, 2.0] + internal_structure: &pon_int_upper + layers: + - name: pon_twall + material: steel + thickness: + grid: [0.0, 1.0] + values: [0.02, 0.02] + # ballasts: + # - variable_flag: False + # material: slurry + # volume: 519 + # grid: [0.0, 0.05] + # - variable_flag: True + # grid: [0.0, 1.0] + # bulkhead: + # material: '' + # thickness: + # grid: [] + # values: [] + Ca: 1.0 + Cd: 1.2 + Cp: 1.0 + # axial_joints: + # - {name: '', grid: 0} + - name: 'upper_pontoon_DS' + joint1: 'downstream_upper_pon' + joint2: 'starboard_upper_pon' + outer_shape: *pon_out + internal_structure: *pon_int_upper + Ca: 1.0 + Cd: 1.2 + Cp: 1.0 + # axial_joints: + # - {name: '', grid: 0} + - name: 'upper_pontoon_UP' + joint1: 'upstream_upper_pon' + joint2: 'port_upper_pon' + outer_shape: *pon_out + internal_structure: *pon_int_upper + Ca: 1.0 + Cd: 1.2 + Cp: 1.0 + # axial_joints: + # - {name: '', grid: 0} + - name: 'upper_pontoon_US' + joint1: 'upstream_upper_pon' + joint2: 'starboard_upper_pon' + outer_shape: *pon_out + internal_structure: *pon_int_upper + Ca: 1.0 + Cd: 1.2 + Cp: 1.0 + # axial_joints: + # - {name: '', grid: 0} + - name: 'upper_pontoon_PS' + joint1: 'port_upper_pon' + joint2: 'starboard_upper_pon' + outer_shape: *pon_out + Ca: 1.0 + Cd: 1.2 + Cp: 1.0 + internal_structure: *pon_int_upper + - name: 'lower_pontoon_DP' + joint1: 'downstream_lower_pon' + joint2: 'port_lower_pon' + outer_shape: *pon_out + internal_structure: &pon_int_lower + layers: + - name: pon_twall + material: steel + thickness: + grid: [0.0, 1.0] + values: [0.02, 0.02] + ballasts: + - variable_flag: True + grid: [0.0, 1.0] + Ca: 1.0 + Cd: 1.2 + Cp: 1.0 + # axial_joints: + # - {name: '', grid: 0} + - name: 'lower_pontoon_DS' + joint1: 'downstream_lower_pon' + joint2: 'starboard_lower_pon' + outer_shape: *pon_out + internal_structure: *pon_int_lower + Ca: 1.0 + Cd: 1.2 + Cp: 1.0 + # axial_joints: + # - {name: '', grid: 0} + - name: 'lower_pontoon_UP' + joint1: 'upstream_lower_pon' + joint2: 'port_lower_pon' + outer_shape: *pon_out + internal_structure: *pon_int_lower + Ca: 1.0 + Cd: 1.2 + Cp: 1.0 + # axial_joints: + # - {name: '', grid: 0} + - name: 'lower_pontoon_US' + joint1: 'upstream_lower_pon' + joint2: 'starboard_lower_pon' + outer_shape: *pon_out + internal_structure: *pon_int_lower + Ca: 1.0 + Cd: 1.2 + Cp: 1.0 + # axial_joints: + # - {name: '', grid: 0} + - name: 'lower_pontoon_PS' + joint1: 'port_lower_pon' + joint2: 'starboard_lower_pon' + outer_shape: *pon_out + internal_structure: *pon_int_upper # no ballast because it fills from one end to other + Ca: 1.0 + Cd: 1.2 + Cp: 1.0 + axial_joints: + - {name: 'lower_brace', grid: 0.5} + - name: 'tower_brace_port' + joint1: 'port_upper_pon' + joint2: 'lower_brace' + outer_shape: *pon_out + internal_structure: *pon_int_lower + Ca: 1.0 + Cd: 1.2 + Cp: 1.0 + - name: 'tower_brace_starboard' + joint1: 'starboard_upper_pon' + joint2: 'lower_brace' + outer_shape: *pon_out + internal_structure: *pon_int_lower + Ca: 1.0 + Cd: 1.2 + Cp: 1.0 + + transition_piece_mass: 0 + transition_piece_cost: 0 + mooring: + nodes: + - {name: 'line1_anchor', node_type: fixed, joint: 'anchor_1', anchor_type: drag_embedment} + - {name: 'line2_anchor', node_type: fixed, joint: 'anchor_2', anchor_type: drag_embedment} + - {name: 'line3_anchor', node_type: fixed, joint: 'anchor_3', anchor_type: drag_embedment} + - {name: 'line4_anchor', node_type: fixed, joint: 'anchor_4', anchor_type: drag_embedment} + - {name: 'line5_anchor', node_type: fixed, joint: 'anchor_5', anchor_type: drag_embedment} + - {name: 'line6_anchor', node_type: fixed, joint: 'anchor_6', anchor_type: drag_embedment} + - {name: 'line1_fairlead', node_type: vessel, joint: 'upstream_lower_col', fairlead_type: rigid} + - {name: 'line2_fairlead', node_type: vessel, joint: 'upstream_lower_col', fairlead_type: rigid} + - {name: 'line3_fairlead', node_type: vessel, joint: 'upstream_lower_col', fairlead_type: rigid} + - {name: 'line4_fairlead', node_type: vessel, joint: 'downstream_lower_col', fairlead_type: rigid} + - {name: 'line5_fairlead', node_type: vessel, joint: 'downstream_lower_col', fairlead_type: rigid} + - {name: 'line6_fairlead', node_type: vessel, joint: 'downstream_lower_col', fairlead_type: rigid} + lines: + - {name: 'line1', node1: 'line1_anchor', node2: 'line1_fairlead', line_type: 'main', unstretched_length: 160} + - {name: 'line2', node1: 'line2_anchor', node2: 'line2_fairlead', line_type: 'main', unstretched_length: 160} + - {name: 'line3', node1: 'line3_anchor', node2: 'line3_fairlead', line_type: 'main', unstretched_length: 160} + - {name: 'line4', node1: 'line4_anchor', node2: 'line4_fairlead', line_type: 'main', unstretched_length: 160} + - {name: 'line5', node1: 'line5_anchor', node2: 'line5_fairlead', line_type: 'main', unstretched_length: 152} + - {name: 'line6', node1: 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E-LT-5500, Epikote MGS RIMR 135/Epicure MGS RIMH 1366 epoxy + source: MSU composites database 3D property tests, Engineering Mechanics of Composite Materials, Daniel, I & Ishai, O., 1994, pg. 34 + orth: 1.0 + rho: 1940.0 + E: [28700000000.0, 16600000000.0, 16700000000.0] + G: [8400000000.0, 3490000000.0, 3490000000.0] + nu: [0.5, 0.0, 0.17] + Xt: [396000000.0, 76400000.0, 15300000.0] + Xc: [448900000.0, 174700000.0, 113200000.0] + S: [103400000.0, 17200000.0, 13200000.0] + m: 10 + GIc: 303 + GIIc: 3446 + alp0: 53 + fvf: 0.57 + fwf: 0.7450682696347697 + ply_t: 0.001 + unit_cost: 2.86 + waste: 0.15 + fiber_density: 2535.5 + area_density_dry: 1.4454324430914534 + component_id: 2 + roll_mass: 181.4368 + - {name: medium_density_foam, description: Airex C70.130 PVC Foam, source: "https://www.3accorematerials.com/uploads/documents/TDS-AIREX-C70-E_1106.pdf", orth: 0.0, rho: 130.0, E: 129200000.0, G: 48946969.696969695, nu: 0.32, Xt: 2083000.0, Xc: 1563000.0, S: 1250000.0, GIc: 303, GIIc: 3446, alp0: 53, component_id: 1, waste: 0.2, unit_cost: 13} + - {name: resin, description: epoxy, E: 1000000.0, nu: 0.3, G: 312500.0, GIc: 0, GIIc: 0, alp0: 0, Xt: 0, Xc: 0, S: 0, rho: 1150.0, alpha: 0.0, orth: 0, unit_cost: 3.63} + - {name: slurry, description: fixed/permanent ballast, E: 1.0, nu: 0.3, G: 1.0, Xt: 0, Xc: 0, S: 0, rho: 5000.0, alpha: 0.0, unit_cost: 1.0, orth: 0.0} + - {name: adhesive, description: Sample adhesive, source: "https://www.nrel.gov/docs/fy19osti/73585.pdf", orth: 0, rho: 1100, E: 4560000.0, nu: 0.49, alpha: 0.0, Xt: 690000.0, Xc: 400000.0, S: 310000.0, G: 1520000.0, unit_cost: 9.0} +control: + supervisory: {Vin: 0.5, Vout: 4.0, maxTS: 60} + pitch: {PC_zeta: !!null '', PC_omega: !!null '', ps_percent: !!null '', max_pitch: !!null '', max_pitch_rate: 0.1745, min_pitch: 0.00088} + torque: {control_type: !!null '', tsr: 7.64, VS_zeta: !!null '', VS_omega: !!null '', max_torque_rate: 1500000.0, VS_minspd: 0.0, VS_maxspd: 1.26711} + setpoint_smooth: {ss_vsgain: !!null '', ss_pcgain: !!null ''} + shutdown: {limit_type: !!null '', limit_value: !!null ''} +environment: {air_density: 1.225, air_dyn_viscosity: 1.7894e-5, air_speed_sound: 1500.0, shear_exp: 0.0, gravity: 9.80665, weib_shape_parameter: 2.0, water_density: 1025.0, water_dyn_viscosity: 0.0013351, soil_shear_modulus: 140000000.0, soil_poisson: 0.4, water_depth: 50.0, air_pressure: 101325.0, air_vapor_pressure: 2500.0, significant_wave_height: 1.0, significant_wave_period: 5.0} +bos: {plant_turbine_spacing: 7, plant_row_spacing: 7, commissioning_pct: 0.01, decommissioning_pct: 0.15, distance_to_substation: 1.0, distance_to_interconnection: 8.5, interconnect_voltage: 130.0, distance_to_site: 115.0, distance_to_landfall: 50.0, port_cost_per_month: 2000000.0, site_auction_price: 100000000.0, site_assessment_plan_cost: 1000000.0, site_assessment_cost: 25000000.0, construction_operations_plan_cost: 2500000.0, boem_review_cost: 0.0, design_install_plan_cost: 2500000.0} +costs: {wake_loss_factor: 0.15, fixed_charge_rate: 0.056, bos_per_kW: 4053.0, opex_per_kW: 137.0, turbine_number: 40.0, labor_rate: 58.8, painting_rate: 30.0, blade_mass_cost_coeff: 14.6, hub_mass_cost_coeff: 3.9, pitch_system_mass_cost_coeff: 22.1, spinner_mass_cost_coeff: 11.1, lss_mass_cost_coeff: 11.9, bearing_mass_cost_coeff: 4.5, gearbox_mass_cost_coeff: 12.9, hss_mass_cost_coeff: 6.8, generator_mass_cost_coeff: 12.4, bedplate_mass_cost_coeff: 2.9, yaw_mass_cost_coeff: 8.3, converter_mass_cost_coeff: 18.8, transformer_mass_cost_coeff: 18.8, hvac_mass_cost_coeff: 124.0, cover_mass_cost_coeff: 5.7, elec_connec_machine_rating_cost_coeff: 41.85, platforms_mass_cost_coeff: 17.1, tower_mass_cost_coeff: 2.9, controls_machine_rating_cost_coeff: 21.15, crane_cost: 12000.0, electricity_price: 0.04, reserve_margin_price: 120.0, capacity_credit: 0.0, benchmark_price: 0.071} diff --git a/examples/Optimization/airfoils/Airfoils.txt b/examples/Optimization/airfoils/Airfoils.txt new file mode 100644 index 00000000..516c3ad3 --- /dev/null +++ b/examples/Optimization/airfoils/Airfoils.txt @@ -0,0 +1,39 @@ +04/10/97 + +Coordinates for the SNL airfoils: + + SNL 0015/47 SNL 0018/50 SNL 0021/50 + X (Y X (Y X (Y +0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 +0.00020 0.00166 0.00337 0.00646 0.00343 0.00790 +0.00508 0.01091 0.01274 0.01431 0.01291 0.01728 +0.01507 0.02060 0.02713 0.02282 0.02740 0.02735 +0.02872 0.02867 0.04621 0.03160 0.04653 0.03771 +0.04729 0.03615 0.06970 0.04042 0.07001 0.04806 +0.07062 0.04329 0.09730 0.04903 0.09753 0.05814 +0.09832 0.05006 0.12870 0.05726 0.12878 0.06772 +0.13002 0.05630 0.16353 0.06491 0.16339 0.07660 +0.16533 0.06192 0.20142 0.07183 0.20098 0.08460 +0.20386 0.06678 0.24193 0.07786 0.24113 0.09152 +0.24517 0.07080 0.28464 0.08283 0.28339 0.09721 +0.28880 0.07383 0.32907 0.08663 0.32730 0.10149 +0.33426 0.07575 0.37471 0.08908 0.37235 0.10417 +0.38104 0.07643 0.42107 0.09000 0.41805 0.10507 +0.42860 0.07556 0.46759 0.08902 0.46384 0.10379 +0.47688 0.07272 0.51422 0.08561 0.50965 0.09968 +0.52610 0.06808 0.56140 0.07982 0.55603 0.09272 +0.57603 0.06216 0.60914 0.07234 0.60311 0.08368 +0.62618 0.05535 0.65698 0.06379 0.65048 0.07323 +0.67600 0.04801 0.70440 0.05462 0.69767 0.06193 +0.72489 0.04046 0.75083 0.04535 0.74412 0.05037 +0.77244 0.03306 0.79560 0.03642 0.78921 0.03911 +0.81734 0.02608 0.83798 0.02827 0.83220 0.02869 +0.85951 0.01979 0.87718 0.02125 0.87224 0.01959 +0.89801 0.01441 0.91233 0.01562 0.90843 0.01217 +0.93212 0.01005 0.94258 0.01150 0.93980 0.00663 +0.96114 0.00676 0.96711 0.00881 0.96541 0.00296 +0.98447 0.00448 0.98519 0.00740 0.98439 0.00095 +0.99685 0.00349 0.99627 0.00687 0.99606 0.00015 +1.00000 0.00000 1.00000 0.00678 1.00000 0.00000 + +The 18/50 was thickened up near the trailing edge so we could actually build it (we can't make a razor-edged extrusion). Although we had to do a similar thing with the other two airfoils when we built models, I don't have those coordinates available. diff --git a/examples/Optimization/airfoils/NACA_0015.dat b/examples/Optimization/airfoils/NACA_0015.dat new file mode 100644 index 00000000..d2fca4f5 --- /dev/null +++ b/examples/Optimization/airfoils/NACA_0015.dat @@ -0,0 +1,1379 @@ +Title: NACA0015 +Thickness to Chord Ratio: 0.15 +Zero Lift AOA (deg): 0.0 +Reverse Camber Direction: 0 + +Reynolds Number: 1e4 +BV Dyn. Stall Model - Positive Stall AOA (deg): 1.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -1.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 5.73 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1 +AOA (deg) CL CD Cm25 +-180.0000 0.0000 0.0250 0.0000 +-175.0000 0.6600 0.0550 0.0000 +-170.0000 0.8500 0.1400 0.0000 +-165.0000 0.6800 0.2300 0.0000 +-160.0000 0.6350 0.3200 0.0000 +-155.0000 0.6700 0.4200 0.0000 +-150.0000 0.7700 0.5750 0.0000 +-145.0000 0.9000 0.7550 0.0000 +-140.0000 0.9800 0.9250 0.0000 +-135.0000 0.9300 1.0850 0.0000 +-130.0000 0.8500 1.2250 0.0000 +-125.0000 0.7600 1.3500 0.0000 +-120.0000 0.6700 1.4650 0.0000 +-115.0000 0.5750 1.5550 0.0000 +-110.0000 0.4500 1.6350 0.0000 +-105.0000 0.3200 1.7000 0.0000 +-100.0000 0.1850 1.7500 0.0000 +-95.0000 0.0500 1.7800 0.0000 +-90.0000 -0.0900 1.8000 0.0000 +-85.0000 -0.2300 1.8000 0.0000 +-80.0000 -0.3650 1.7800 0.0000 +-75.0000 -0.5000 1.7350 0.0000 +-70.0000 -0.6300 1.6650 0.0000 +-65.0000 -0.7600 1.5750 0.0000 +-60.0000 -0.8750 1.4700 0.0000 +-55.0000 -0.9550 1.3450 0.0000 +-50.0000 -1.0200 1.2150 0.0000 +-45.0000 -1.0500 1.0750 0.0000 +-40.0000 -1.0350 0.9200 0.0000 +-35.0000 -0.9800 0.7450 0.0000 +-30.0000 -0.8550 0.5700 0.0000 +-27.0000 -0.8174 0.4600 0.0000 +-26.0000 -0.7639 0.4320 0.0000 +-25.0000 -0.7099 0.4050 0.0000 +-24.0000 -0.6559 0.3790 0.0000 +-23.0000 -0.6019 0.3540 0.0000 +-22.0000 -0.5479 0.3290 0.0000 +-21.0000 -0.4939 0.3050 0.0000 +-20.0000 -0.4399 0.2820 0.0000 +-19.0000 -0.3859 0.2600 0.0000 +-18.0000 -0.3319 0.2380 0.0000 +-17.0000 -0.2780 0.2170 0.0000 +-16.0000 -0.2242 0.1960 0.0000 +-15.0000 -0.1706 0.1770 0.0000 +-14.0000 -0.1172 0.1580 0.0000 +-13.0000 -0.0649 0.1400 0.0000 +-12.0000 -0.0138 0.1230 0.0000 +-11.0000 0.0348 0.1070 0.0000 +-10.0000 0.0791 0.0910 0.0000 +-9.0000 0.1194 0.0770 0.0000 +-8.0000 0.1484 0.0640 0.0000 +-7.0000 0.1517 0.0510 0.0000 +-6.0000 0.0781 0.0400 0.0000 +-5.0000 -0.0162 0.0393 0.0000 +-4.0000 -0.0581 0.0383 0.0000 +-3.0000 -0.0725 0.0373 0.0000 +-2.0000 -0.0715 0.0366 0.0000 +-1.0000 -0.0434 0.0362 0.0000 +0.0000 0.0000 0.0360 0.0000 +1.0000 0.0434 0.0362 0.0000 +2.0000 0.0715 0.0366 0.0000 +3.0000 0.0725 0.0373 0.0000 +4.0000 0.0581 0.0383 0.0000 +5.0000 0.0162 0.0393 0.0000 +6.0000 -0.0781 0.0400 0.0000 +7.0000 -0.1517 0.0510 0.0000 +8.0000 -0.1484 0.0640 0.0000 +9.0000 -0.1194 0.0770 0.0000 +10.0000 -0.0791 0.0910 0.0000 +11.0000 -0.0348 0.1070 0.0000 +12.0000 0.0138 0.1230 0.0000 +13.0000 0.0649 0.1400 0.0000 +14.0000 0.1172 0.1580 0.0000 +15.0000 0.1706 0.1770 0.0000 +16.0000 0.2242 0.1960 0.0000 +17.0000 0.2780 0.2170 0.0000 +18.0000 0.3319 0.2380 0.0000 +19.0000 0.3859 0.2600 0.0000 +20.0000 0.4399 0.2820 0.0000 +21.0000 0.4939 0.3050 0.0000 +22.0000 0.5479 0.3290 0.0000 +23.0000 0.6019 0.3540 0.0000 +24.0000 0.6559 0.3790 0.0000 +25.0000 0.7099 0.4050 0.0000 +26.0000 0.7639 0.4320 0.0000 +27.0000 0.8174 0.4600 0.0000 +30.0000 0.8550 0.5700 0.0000 +35.0000 0.9800 0.7450 0.0000 +40.0000 1.0350 0.9200 0.0000 +45.0000 1.0500 1.0750 0.0000 +50.0000 1.0200 1.2150 0.0000 +55.0000 0.9550 1.3450 0.0000 +60.0000 0.8750 1.4700 0.0000 +65.0000 0.7600 1.5750 0.0000 +70.0000 0.6300 1.6650 0.0000 +75.0000 0.5000 1.7350 0.0000 +80.0000 0.3650 1.7800 0.0000 +85.0000 0.2300 1.8000 0.0000 +90.0000 0.0900 1.8000 0.0000 +95.0000 -0.0500 1.7800 0.0000 +100.0000 -0.1850 1.7500 0.0000 +105.0000 -0.3200 1.7000 0.0000 +110.0000 -0.4500 1.6350 0.0000 +115.0000 -0.5750 1.5550 0.0000 +120.0000 -0.6700 1.4650 0.0000 +125.0000 -0.7600 1.3500 0.0000 +130.0000 -0.8500 1.2250 0.0000 +135.0000 -0.9300 1.0850 0.0000 +140.0000 -0.9800 0.9250 0.0000 +145.0000 -0.9000 0.7550 0.0000 +150.0000 -0.7700 0.5750 0.0000 +155.0000 -0.6700 0.4200 0.0000 +160.0000 -0.6350 0.3200 0.0000 +165.0000 -0.6800 0.2300 0.0000 +170.0000 -0.8500 0.1400 0.0000 +175.0000 -0.6600 0.0550 0.0000 +180.0000 0.0000 0.0250 0.0000 + +Reynolds Number: 2e4 +BV Dyn. Stall Model - Positive Stall AOA (deg): 2.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -2.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 5.73 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1 +AOA (deg) CL CD Cm25 +-180.0000 0.0000 0.0250 0.0000 +-175.0000 0.6600 0.0550 0.0000 +-170.0000 0.8500 0.1400 0.0000 +-165.0000 0.6800 0.2300 0.0000 +-160.0000 0.6350 0.3200 0.0000 +-155.0000 0.6700 0.4200 0.0000 +-150.0000 0.7700 0.5750 0.0000 +-145.0000 0.9000 0.7550 0.0000 +-140.0000 0.9800 0.9250 0.0000 +-135.0000 0.9300 1.0850 0.0000 +-130.0000 0.8500 1.2250 0.0000 +-125.0000 0.7600 1.3500 0.0000 +-120.0000 0.6700 1.4650 0.0000 +-115.0000 0.5750 1.5550 0.0000 +-110.0000 0.4500 1.6350 0.0000 +-105.0000 0.3200 1.7000 0.0000 +-100.0000 0.1850 1.7500 0.0000 +-95.0000 0.0500 1.7800 0.0000 +-90.0000 -0.0900 1.8000 0.0000 +-85.0000 -0.2300 1.8000 0.0000 +-80.0000 -0.3650 1.7800 0.0000 +-75.0000 -0.5000 1.7350 0.0000 +-70.0000 -0.6300 1.6650 0.0000 +-65.0000 -0.7600 1.5750 0.0000 +-60.0000 -0.8750 1.4700 0.0000 +-55.0000 -0.9550 1.3450 0.0000 +-50.0000 -1.0200 1.2150 0.0000 +-45.0000 -1.0500 1.0750 0.0000 +-40.0000 -1.0350 0.9200 0.0000 +-35.0000 -0.9800 0.7450 0.0000 +-30.0000 -0.8550 0.5700 0.0000 +-27.0000 -0.8191 0.4600 0.0000 +-26.0000 -0.7649 0.4320 0.0000 +-25.0000 -0.7109 0.4050 0.0000 +-24.0000 -0.6569 0.3790 0.0000 +-23.0000 -0.6029 0.3540 0.0000 +-22.0000 -0.5489 0.3290 0.0000 +-21.0000 -0.4949 0.3050 0.0000 +-20.0000 -0.4409 0.2820 0.0000 +-19.0000 -0.3869 0.2600 0.0000 +-18.0000 -0.3331 0.2380 0.0000 +-17.0000 -0.2792 0.2170 0.0000 +-16.0000 -0.2256 0.1960 0.0000 +-15.0000 -0.1721 0.1770 0.0000 +-14.0000 -0.1193 0.1580 0.0000 +-13.0000 -0.0678 0.1400 0.0000 +-12.0000 -0.0173 0.1230 0.0000 +-11.0000 0.0300 0.1070 0.0000 +-10.0000 0.0728 0.0910 0.0000 +-9.0000 0.1050 0.0770 0.0000 +-8.0000 0.1104 0.0640 0.0000 +-7.0000 -0.0570 0.0510 0.0000 +-6.0000 -0.3001 0.0410 0.0000 +-5.0000 -0.3359 0.0303 0.0000 +-4.0000 -0.3041 0.0290 0.0000 +-3.0000 -0.2452 0.0279 0.0000 +-2.0000 -0.1740 0.0271 0.0000 +-1.0000 -0.0891 0.0267 0.0000 +0.0000 0.0000 0.0265 0.0000 +1.0000 0.0891 0.0267 0.0000 +2.0000 0.1740 0.0271 0.0000 +3.0000 0.2452 0.0279 0.0000 +4.0000 0.3041 0.0290 0.0000 +5.0000 0.3359 0.0303 0.0000 +6.0000 0.3001 0.0410 0.0000 +7.0000 0.0570 0.0510 0.0000 +8.0000 -0.1104 0.0640 0.0000 +9.0000 -0.1050 0.0770 0.0000 +10.0000 -0.0728 0.0910 0.0000 +11.0000 -0.0300 0.1070 0.0000 +12.0000 0.0173 0.1230 0.0000 +13.0000 0.0678 0.1400 0.0000 +14.0000 0.1193 0.1580 0.0000 +15.0000 0.1721 0.1770 0.0000 +16.0000 0.2256 0.1960 0.0000 +17.0000 0.2792 0.2170 0.0000 +18.0000 0.3331 0.2380 0.0000 +19.0000 0.3869 0.2600 0.0000 +20.0000 0.4409 0.2820 0.0000 +21.0000 0.4949 0.3050 0.0000 +22.0000 0.5489 0.3290 0.0000 +23.0000 0.6029 0.3540 0.0000 +24.0000 0.6569 0.3790 0.0000 +25.0000 0.7109 0.4050 0.0000 +26.0000 0.7649 0.4320 0.0000 +27.0000 0.8191 0.4600 0.0000 +30.0000 0.8550 0.5700 0.0000 +35.0000 0.9800 0.7450 0.0000 +40.0000 1.0350 0.9200 0.0000 +45.0000 1.0500 1.0750 0.0000 +50.0000 1.0200 1.2150 0.0000 +55.0000 0.9550 1.3450 0.0000 +60.0000 0.8750 1.4700 0.0000 +65.0000 0.7600 1.5750 0.0000 +70.0000 0.6300 1.6650 0.0000 +75.0000 0.5000 1.7350 0.0000 +80.0000 0.3650 1.7800 0.0000 +85.0000 0.2300 1.8000 0.0000 +90.0000 0.0900 1.8000 0.0000 +95.0000 -0.0500 1.7800 0.0000 +100.0000 -0.1850 1.7500 0.0000 +105.0000 -0.3200 1.7000 0.0000 +110.0000 -0.4500 1.6350 0.0000 +115.0000 -0.5750 1.5550 0.0000 +120.0000 -0.6700 1.4650 0.0000 +125.0000 -0.7600 1.3500 0.0000 +130.0000 -0.8500 1.2250 0.0000 +135.0000 -0.9300 1.0850 0.0000 +140.0000 -0.9800 0.9250 0.0000 +145.0000 -0.9000 0.7550 0.0000 +150.0000 -0.7700 0.5750 0.0000 +155.0000 -0.6700 0.4200 0.0000 +160.0000 -0.6350 0.3200 0.0000 +165.0000 -0.6800 0.2300 0.0000 +170.0000 -0.8500 0.1400 0.0000 +175.0000 -0.6600 0.0550 0.0000 +180.0000 0.0000 0.0250 0.0000 + +Reynolds Number: 4e4 +BV Dyn. Stall Model - Positive Stall AOA (deg): 4.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -4.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 5.879 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 0.72 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -0.72 +AOA (deg) CL CD Cm25 +-180.0000 0.0000 0.0250 0.0000 +-175.0000 0.6600 0.0550 0.0000 +-170.0000 0.8500 0.1400 0.0000 +-165.0000 0.6800 0.2300 0.0000 +-160.0000 0.6350 0.3200 0.0000 +-155.0000 0.6700 0.4200 0.0000 +-150.0000 0.7700 0.5750 0.0000 +-145.0000 0.9000 0.7550 0.0000 +-140.0000 0.9800 0.9250 0.0000 +-135.0000 0.9300 1.0850 0.0000 +-130.0000 0.8500 1.2250 0.0000 +-125.0000 0.7600 1.3500 0.0000 +-120.0000 0.6700 1.4650 0.0000 +-115.0000 0.5750 1.5550 0.0000 +-110.0000 0.4500 1.6350 0.0000 +-105.0000 0.3200 1.7000 0.0000 +-100.0000 0.1850 1.7500 0.0000 +-95.0000 0.0500 1.7800 0.0000 +-90.0000 -0.0900 1.8000 0.0000 +-85.0000 -0.2300 1.8000 0.0000 +-80.0000 -0.3650 1.7800 0.0000 +-75.0000 -0.5000 1.7350 0.0000 +-70.0000 -0.6300 1.6650 0.0000 +-65.0000 -0.7600 1.5750 0.0000 +-60.0000 -0.8750 1.4700 0.0000 +-55.0000 -0.9550 1.3450 0.0000 +-50.0000 -1.0200 1.2150 0.0000 +-45.0000 -1.0500 1.0750 0.0000 +-40.0000 -1.0350 0.9200 0.0000 +-35.0000 -0.9800 0.7450 0.0000 +-30.0000 -0.8550 0.5700 0.0000 +-27.0000 -0.8222 0.4600 0.0000 +-26.0000 -0.7666 0.4320 0.0000 +-25.0000 -0.7125 0.4050 0.0000 +-24.0000 -0.6585 0.3790 0.0000 +-23.0000 -0.6045 0.3540 0.0000 +-22.0000 -0.5506 0.3290 0.0000 +-21.0000 -0.4966 0.3050 0.0000 +-20.0000 -0.4427 0.2820 0.0000 +-19.0000 -0.3889 0.2600 0.0000 +-18.0000 -0.3351 0.2380 0.0000 +-17.0000 -0.2815 0.2170 0.0000 +-16.0000 -0.2280 0.1960 0.0000 +-15.0000 -0.1756 0.1770 0.0000 +-14.0000 -0.1244 0.1580 0.0000 +-13.0000 -0.0741 0.1400 0.0000 +-12.0000 -0.0261 0.1230 0.0000 +-11.0000 0.0144 0.1070 0.0000 +-10.0000 0.0413 0.0910 0.0000 +-9.0000 -0.0433 0.0770 0.0000 +-8.0000 -0.4663 0.0520 0.0000 +-7.0000 -0.5730 0.0267 0.0000 +-6.0000 -0.5551 0.0249 0.0000 +-5.0000 -0.4871 0.0232 0.0000 +-4.0000 -0.4017 0.0219 0.0000 +-3.0000 -0.3078 0.0209 0.0000 +-2.0000 -0.2099 0.0202 0.0000 +-1.0000 -0.1054 0.0198 0.0000 +0.0000 0.0000 0.0196 0.0000 +1.0000 0.1054 0.0198 0.0000 +2.0000 0.2099 0.0202 0.0000 +3.0000 0.3078 0.0209 0.0000 +4.0000 0.4017 0.0219 0.0000 +5.0000 0.4871 0.0232 0.0000 +6.0000 0.5551 0.0249 0.0000 +7.0000 0.5730 0.0267 0.0000 +8.0000 0.4663 0.0520 0.0000 +9.0000 0.0433 0.0770 0.0000 +10.0000 -0.0413 0.0910 0.0000 +11.0000 -0.0144 0.1070 0.0000 +12.0000 0.0261 0.1230 0.0000 +13.0000 0.0741 0.1400 0.0000 +14.0000 0.1244 0.1580 0.0000 +15.0000 0.1756 0.1770 0.0000 +16.0000 0.2280 0.1960 0.0000 +17.0000 0.2815 0.2170 0.0000 +18.0000 0.3351 0.2380 0.0000 +19.0000 0.3889 0.2600 0.0000 +20.0000 0.4427 0.2820 0.0000 +21.0000 0.4966 0.3050 0.0000 +22.0000 0.5506 0.3290 0.0000 +23.0000 0.6045 0.3540 0.0000 +24.0000 0.6585 0.3790 0.0000 +25.0000 0.7125 0.4050 0.0000 +26.0000 0.7666 0.4320 0.0000 +27.0000 0.8222 0.4600 0.0000 +30.0000 0.8550 0.5700 0.0000 +35.0000 0.9800 0.7450 0.0000 +40.0000 1.0350 0.9200 0.0000 +45.0000 1.0500 1.0750 0.0000 +50.0000 1.0200 1.2150 0.0000 +55.0000 0.9550 1.3450 0.0000 +60.0000 0.8750 1.4700 0.0000 +65.0000 0.7600 1.5750 0.0000 +70.0000 0.6300 1.6650 0.0000 +75.0000 0.5000 1.7350 0.0000 +80.0000 0.3650 1.7800 0.0000 +85.0000 0.2300 1.8000 0.0000 +90.0000 0.0900 1.8000 0.0000 +95.0000 -0.0500 1.7800 0.0000 +100.0000 -0.1850 1.7500 0.0000 +105.0000 -0.3200 1.7000 0.0000 +110.0000 -0.4500 1.6350 0.0000 +115.0000 -0.5750 1.5550 0.0000 +120.0000 -0.6700 1.4650 0.0000 +125.0000 -0.7600 1.3500 0.0000 +130.0000 -0.8500 1.2250 0.0000 +135.0000 -0.9300 1.0850 0.0000 +140.0000 -0.9800 0.9250 0.0000 +145.0000 -0.9000 0.7550 0.0000 +150.0000 -0.7700 0.5750 0.0000 +155.0000 -0.6700 0.4200 0.0000 +160.0000 -0.6350 0.3200 0.0000 +165.0000 -0.6800 0.2300 0.0000 +170.0000 -0.8500 0.1400 0.0000 +175.0000 -0.6600 0.0550 0.0000 +180.0000 0.0000 0.0250 0.0000 + +Reynolds Number: 8e4 +BV Dyn. Stall Model - Positive Stall AOA (deg): 5.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -5.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 0.88 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -0.88 +AOA (deg) CL CD Cm25 +-180.0000 0.0000 0.0250 0.0000 +-175.0000 0.6600 0.0550 0.0000 +-170.0000 0.8500 0.1400 0.0000 +-165.0000 0.6800 0.2300 0.0000 +-160.0000 0.6350 0.3200 0.0000 +-155.0000 0.6700 0.4200 0.0000 +-150.0000 0.7700 0.5750 0.0000 +-145.0000 0.9000 0.7550 0.0000 +-140.0000 0.9800 0.9250 0.0000 +-135.0000 0.9300 1.0850 0.0000 +-130.0000 0.8500 1.2250 0.0000 +-125.0000 0.7600 1.3500 0.0000 +-120.0000 0.6700 1.4650 0.0000 +-115.0000 0.5750 1.5550 0.0000 +-110.0000 0.4500 1.6350 0.0000 +-105.0000 0.3200 1.7000 0.0000 +-100.0000 0.1850 1.7500 0.0000 +-95.0000 0.0500 1.7800 0.0000 +-90.0000 -0.0900 1.8000 0.0000 +-85.0000 -0.2300 1.8000 0.0000 +-80.0000 -0.3650 1.7800 0.0000 +-75.0000 -0.5000 1.7350 0.0000 +-70.0000 -0.6300 1.6650 0.0000 +-65.0000 -0.7600 1.5750 0.0000 +-60.0000 -0.8750 1.4700 0.0000 +-55.0000 -0.9550 1.3450 0.0000 +-50.0000 -1.0200 1.2150 0.0000 +-45.0000 -1.0500 1.0750 0.0000 +-40.0000 -1.0350 0.9200 0.0000 +-35.0000 -0.9800 0.7450 0.0000 +-30.0000 -0.8550 0.5700 0.0000 +-27.0000 -0.8277 0.4600 0.0000 +-26.0000 -0.7700 0.4320 0.0000 +-25.0000 -0.7156 0.4050 0.0000 +-24.0000 -0.6617 0.3790 0.0000 +-23.0000 -0.6078 0.3540 0.0000 +-22.0000 -0.5539 0.3290 0.0000 +-21.0000 -0.5001 0.3050 0.0000 +-20.0000 -0.4463 0.2820 0.0000 +-19.0000 -0.3927 0.2600 0.0000 +-18.0000 -0.3393 0.2380 0.0000 +-17.0000 -0.2873 0.2170 0.0000 +-16.0000 -0.2364 0.1960 0.0000 +-15.0000 -0.1861 0.1770 0.0000 +-14.0000 -0.1382 0.1580 0.0000 +-13.0000 -0.0967 0.1400 0.0000 +-12.0000 -0.0749 0.1230 0.0000 +-11.0000 -0.1642 0.0760 0.0000 +-10.0000 -0.5122 0.0277 0.0000 +-9.0000 -0.6969 0.0255 0.0000 +-8.0000 -0.7189 0.0234 0.0000 +-7.0000 -0.6760 0.0214 0.0000 +-6.0000 -0.6048 0.0197 0.0000 +-5.0000 -0.5180 0.0181 0.0000 +-4.0000 -0.4186 0.0168 0.0000 +-3.0000 -0.3300 0.0156 0.0000 +-2.0000 -0.2200 0.0151 0.0000 +-1.0000 -0.1100 0.0148 0.0000 +0.0000 0.0000 0.0147 0.0000 +1.0000 0.1100 0.0148 0.0000 +2.0000 0.2200 0.0151 0.0000 +3.0000 0.3300 0.0156 0.0000 +4.0000 0.4186 0.0168 0.0000 +5.0000 0.5180 0.0181 0.0000 +6.0000 0.6048 0.0197 0.0000 +7.0000 0.6760 0.0214 0.0000 +8.0000 0.7189 0.0234 0.0000 +9.0000 0.6969 0.0255 0.0000 +10.0000 0.5122 0.0277 0.0000 +11.0000 0.1642 0.0760 0.0000 +12.0000 0.0749 0.1230 0.0000 +13.0000 0.0967 0.1400 0.0000 +14.0000 0.1382 0.1580 0.0000 +15.0000 0.1861 0.1770 0.0000 +16.0000 0.2364 0.1960 0.0000 +17.0000 0.2873 0.2170 0.0000 +18.0000 0.3393 0.2380 0.0000 +19.0000 0.3927 0.2600 0.0000 +20.0000 0.4463 0.2820 0.0000 +21.0000 0.5001 0.3050 0.0000 +22.0000 0.5539 0.3290 0.0000 +23.0000 0.6078 0.3540 0.0000 +24.0000 0.6617 0.3790 0.0000 +25.0000 0.7156 0.4050 0.0000 +26.0000 0.7700 0.4320 0.0000 +27.0000 0.8277 0.4600 0.0000 +30.0000 0.8550 0.5700 0.0000 +35.0000 0.9800 0.7450 0.0000 +40.0000 1.0350 0.9200 0.0000 +45.0000 1.0500 1.0750 0.0000 +50.0000 1.0200 1.2150 0.0000 +55.0000 0.9550 1.3450 0.0000 +60.0000 0.8750 1.4700 0.0000 +65.0000 0.7600 1.5750 0.0000 +70.0000 0.6300 1.6650 0.0000 +75.0000 0.5000 1.7350 0.0000 +80.0000 0.3650 1.7800 0.0000 +85.0000 0.2300 1.8000 0.0000 +90.0000 0.0900 1.8000 0.0000 +95.0000 -0.0500 1.7800 0.0000 +100.0000 -0.1850 1.7500 0.0000 +105.0000 -0.3200 1.7000 0.0000 +110.0000 -0.4500 1.6350 0.0000 +115.0000 -0.5750 1.5550 0.0000 +120.0000 -0.6700 1.4650 0.0000 +125.0000 -0.7600 1.3500 0.0000 +130.0000 -0.8500 1.2250 0.0000 +135.0000 -0.9300 1.0850 0.0000 +140.0000 -0.9800 0.9250 0.0000 +145.0000 -0.9000 0.7550 0.0000 +150.0000 -0.7700 0.5750 0.0000 +155.0000 -0.6700 0.4200 0.0000 +160.0000 -0.6350 0.3200 0.0000 +165.0000 -0.6800 0.2300 0.0000 +170.0000 -0.8500 0.1400 0.0000 +175.0000 -0.6600 0.0550 0.0000 +180.0000 0.0000 0.0250 0.0000 + +Reynolds Number: 1.6e5 +BV Dyn. Stall Model - Positive Stall AOA (deg): 5.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -5.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 0.99 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -0.99 +AOA (deg) CL CD Cm25 +-180.0000 0.0000 0.0250 0.0000 +-175.0000 0.6600 0.0550 0.0000 +-170.0000 0.8500 0.1400 0.0000 +-165.0000 0.6800 0.2300 0.0000 +-160.0000 0.6350 0.3200 0.0000 +-155.0000 0.6700 0.4200 0.0000 +-150.0000 0.7700 0.5750 0.0000 +-145.0000 0.9000 0.7550 0.0000 +-140.0000 0.9800 0.9250 0.0000 +-135.0000 0.9300 1.0850 0.0000 +-130.0000 0.8500 1.2250 0.0000 +-125.0000 0.7600 1.3500 0.0000 +-120.0000 0.6700 1.4650 0.0000 +-115.0000 0.5750 1.5550 0.0000 +-110.0000 0.4500 1.6350 0.0000 +-105.0000 0.3200 1.7000 0.0000 +-100.0000 0.1850 1.7500 0.0000 +-95.0000 0.0500 1.7800 0.0000 +-90.0000 -0.0900 1.8000 0.0000 +-85.0000 -0.2300 1.8000 0.0000 +-80.0000 -0.3650 1.7800 0.0000 +-75.0000 -0.5000 1.7350 0.0000 +-70.0000 -0.6300 1.6650 0.0000 +-65.0000 -0.7600 1.5750 0.0000 +-60.0000 -0.8750 1.4700 0.0000 +-55.0000 -0.9550 1.3450 0.0000 +-50.0000 -1.0200 1.2150 0.0000 +-45.0000 -1.0500 1.0750 0.0000 +-40.0000 -1.0350 0.9200 0.0000 +-35.0000 -0.9800 0.7450 0.0000 +-30.0000 -0.8550 0.5700 0.0000 +-27.0000 -0.8382 0.4600 0.0000 +-26.0000 -0.7771 0.4320 0.0000 +-25.0000 -0.7224 0.4050 0.0000 +-24.0000 -0.6685 0.3790 0.0000 +-23.0000 -0.6148 0.3540 0.0000 +-22.0000 -0.5611 0.3290 0.0000 +-21.0000 -0.5087 0.3050 0.0000 +-20.0000 -0.4575 0.2820 0.0000 +-19.0000 -0.4066 0.2600 0.0000 +-18.0000 -0.3567 0.2380 0.0000 +-17.0000 -0.3098 0.2170 0.0000 +-16.0000 -0.2665 0.1970 0.0000 +-15.0000 -0.2376 0.1770 0.0000 +-14.0000 -0.2371 0.1040 0.0000 +-13.0000 -0.3548 0.0302 0.0000 +-12.0000 -0.5936 0.0281 0.0000 +-11.0000 -0.7623 0.0256 0.0000 +-10.0000 -0.8322 0.0233 0.0000 +-9.0000 -0.8311 0.0212 0.0000 +-8.0000 -0.7851 0.0193 0.0000 +-7.0000 -0.7150 0.0176 0.0000 +-6.0000 -0.6299 0.0160 0.0000 +-5.0000 -0.5500 0.0142 0.0000 +-4.0000 -0.4400 0.0132 0.0000 +-3.0000 -0.3300 0.0124 0.0000 +-2.0000 -0.2200 0.0120 0.0000 +-1.0000 -0.1100 0.0117 0.0000 +0.0000 0.0000 0.0116 0.0000 +1.0000 0.1100 0.0117 0.0000 +2.0000 0.2200 0.0120 0.0000 +3.0000 0.3300 0.0124 0.0000 +4.0000 0.4400 0.0132 0.0000 +5.0000 0.5500 0.0142 0.0000 +6.0000 0.6299 0.0160 0.0000 +7.0000 0.7150 0.0176 0.0000 +8.0000 0.7851 0.0193 0.0000 +9.0000 0.8311 0.0212 0.0000 +10.0000 0.8322 0.0233 0.0000 +11.0000 0.7623 0.0256 0.0000 +12.0000 0.5936 0.0281 0.0000 +13.0000 0.3548 0.0302 0.0000 +14.0000 0.2371 0.1040 0.0000 +15.0000 0.2376 0.1770 0.0000 +16.0000 0.2665 0.1970 0.0000 +17.0000 0.3098 0.2170 0.0000 +18.0000 0.3567 0.2380 0.0000 +19.0000 0.4066 0.2600 0.0000 +20.0000 0.4575 0.2820 0.0000 +21.0000 0.5087 0.3050 0.0000 +22.0000 0.5611 0.3290 0.0000 +23.0000 0.6148 0.3540 0.0000 +24.0000 0.6685 0.3790 0.0000 +25.0000 0.7224 0.4050 0.0000 +26.0000 0.7771 0.4320 0.0000 +27.0000 0.8382 0.4600 0.0000 +30.0000 0.8550 0.5700 0.0000 +35.0000 0.9800 0.7450 0.0000 +40.0000 1.0350 0.9200 0.0000 +45.0000 1.0500 1.0750 0.0000 +50.0000 1.0200 1.2150 0.0000 +55.0000 0.9550 1.3450 0.0000 +60.0000 0.8750 1.4700 0.0000 +65.0000 0.7600 1.5750 0.0000 +70.0000 0.6300 1.6650 0.0000 +75.0000 0.5000 1.7350 0.0000 +80.0000 0.3650 1.7800 0.0000 +85.0000 0.2300 1.8000 0.0000 +90.0000 0.0900 1.8000 0.0000 +95.0000 -0.0500 1.7800 0.0000 +100.0000 -0.1850 1.7500 0.0000 +105.0000 -0.3200 1.7000 0.0000 +110.0000 -0.4500 1.6350 0.0000 +115.0000 -0.5750 1.5550 0.0000 +120.0000 -0.6700 1.4650 0.0000 +125.0000 -0.7600 1.3500 0.0000 +130.0000 -0.8500 1.2250 0.0000 +135.0000 -0.9300 1.0850 0.0000 +140.0000 -0.9800 0.9250 0.0000 +145.0000 -0.9000 0.7550 0.0000 +150.0000 -0.7700 0.5750 0.0000 +155.0000 -0.6700 0.4200 0.0000 +160.0000 -0.6350 0.3200 0.0000 +165.0000 -0.6800 0.2300 0.0000 +170.0000 -0.8500 0.1400 0.0000 +175.0000 -0.6600 0.0550 0.0000 +180.0000 0.0000 0.0250 0.0000 + +Reynolds Number: 3.6e5 +BV Dyn. Stall Model - Positive Stall AOA (deg): 6.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -6.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.21 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.21 +AOA (deg) CL CD Cm25 +-180.0000 0.0000 0.0250 0.0000 +-175.0000 0.6600 0.0550 0.0000 +-170.0000 0.8500 0.1400 0.0000 +-165.0000 0.6800 0.2300 0.0000 +-160.0000 0.6350 0.3200 0.0000 +-155.0000 0.6700 0.4200 0.0000 +-150.0000 0.7700 0.5750 0.0000 +-145.0000 0.9000 0.7550 0.0000 +-140.0000 0.9800 0.9250 0.0000 +-135.0000 0.9300 1.0850 0.0000 +-130.0000 0.8500 1.2250 0.0000 +-125.0000 0.7600 1.3500 0.0000 +-120.0000 0.6700 1.4650 0.0000 +-115.0000 0.5750 1.5550 0.0000 +-110.0000 0.4500 1.6350 0.0000 +-105.0000 0.3200 1.7000 0.0000 +-100.0000 0.1850 1.7500 0.0000 +-95.0000 0.0500 1.7800 0.0000 +-90.0000 -0.0900 1.8000 0.0000 +-85.0000 -0.2300 1.8000 0.0000 +-80.0000 -0.3650 1.7800 0.0000 +-75.0000 -0.5000 1.7350 0.0000 +-70.0000 -0.6300 1.6650 0.0000 +-65.0000 -0.7600 1.5750 0.0000 +-60.0000 -0.8750 1.4700 0.0000 +-55.0000 -0.9550 1.3450 0.0000 +-50.0000 -1.0200 1.2150 0.0000 +-45.0000 -1.0500 1.0750 0.0000 +-40.0000 -1.0350 0.9200 0.0000 +-35.0000 -0.9800 0.7450 0.0000 +-30.0000 -0.8550 0.5700 0.0000 +-27.0000 -0.8788 0.4600 0.0000 +-26.0000 -0.8055 0.4320 0.0000 +-25.0000 -0.7511 0.4050 0.0000 +-24.0000 -0.7015 0.3790 0.0000 +-23.0000 -0.6528 0.3540 0.0000 +-22.0000 -0.6045 0.3290 0.0000 +-21.0000 -0.5616 0.3050 0.0000 +-20.0000 -0.5247 0.2820 0.0000 +-19.0000 -0.4908 0.2600 0.0000 +-18.0000 -0.4782 0.2380 0.0000 +-17.0000 -0.4851 0.2170 0.0000 +-16.0000 -0.5384 0.1240 0.0000 +-15.0000 -0.6350 0.0312 0.0000 +-14.0000 -0.7483 0.0283 0.0000 +-13.0000 -0.8562 0.0257 0.0000 +-12.0000 -0.9285 0.0233 0.0000 +-11.0000 -0.9572 0.0211 0.0000 +-10.0000 -0.9440 0.0191 0.0000 +-9.0000 -0.8946 0.0173 0.0000 +-8.0000 -0.8240 0.0157 0.0000 +-7.0000 -0.7390 0.0143 0.0000 +-6.0000 -0.6600 0.0126 0.0000 +-5.0000 -0.5500 0.0114 0.0000 +-4.0000 -0.4400 0.0105 0.0000 +-3.0000 -0.3300 0.0098 0.0000 +-2.0000 -0.2200 0.0094 0.0000 +-1.0000 -0.1100 0.0092 0.0000 +0.0000 0.0000 0.0091 0.0000 +1.0000 0.1100 0.0092 0.0000 +2.0000 0.2200 0.0094 0.0000 +3.0000 0.3300 0.0098 0.0000 +4.0000 0.4400 0.0105 0.0000 +5.0000 0.5500 0.0114 0.0000 +6.0000 0.6600 0.0126 0.0000 +7.0000 0.7390 0.0143 0.0000 +8.0000 0.8240 0.0157 0.0000 +9.0000 0.8946 0.0173 0.0000 +10.0000 0.9440 0.0191 0.0000 +11.0000 0.9572 0.0211 0.0000 +12.0000 0.9285 0.0233 0.0000 +13.0000 0.8562 0.0257 0.0000 +14.0000 0.7483 0.0283 0.0000 +15.0000 0.6350 0.0312 0.0000 +16.0000 0.5384 0.1240 0.0000 +17.0000 0.4851 0.2170 0.0000 +18.0000 0.4782 0.2380 0.0000 +19.0000 0.4908 0.2600 0.0000 +20.0000 0.5247 0.2820 0.0000 +21.0000 0.5616 0.3050 0.0000 +22.0000 0.6045 0.3290 0.0000 +23.0000 0.6528 0.3540 0.0000 +24.0000 0.7015 0.3790 0.0000 +25.0000 0.7511 0.4050 0.0000 +26.0000 0.8055 0.4320 0.0000 +27.0000 0.8788 0.4600 0.0000 +30.0000 0.8550 0.5700 0.0000 +35.0000 0.9800 0.7450 0.0000 +40.0000 1.0350 0.9200 0.0000 +45.0000 1.0500 1.0750 0.0000 +50.0000 1.0200 1.2150 0.0000 +55.0000 0.9550 1.3450 0.0000 +60.0000 0.8750 1.4700 0.0000 +65.0000 0.7600 1.5750 0.0000 +70.0000 0.6300 1.6650 0.0000 +75.0000 0.5000 1.7350 0.0000 +80.0000 0.3650 1.7800 0.0000 +85.0000 0.2300 1.8000 0.0000 +90.0000 0.0900 1.8000 0.0000 +95.0000 -0.0500 1.7800 0.0000 +100.0000 -0.1850 1.7500 0.0000 +105.0000 -0.3200 1.7000 0.0000 +110.0000 -0.4500 1.6350 0.0000 +115.0000 -0.5750 1.5550 0.0000 +120.0000 -0.6700 1.4650 0.0000 +125.0000 -0.7600 1.3500 0.0000 +130.0000 -0.8500 1.2250 0.0000 +135.0000 -0.9300 1.0850 0.0000 +140.0000 -0.9800 0.9250 0.0000 +145.0000 -0.9000 0.7550 0.0000 +150.0000 -0.7700 0.5750 0.0000 +155.0000 -0.6700 0.4200 0.0000 +160.0000 -0.6350 0.3200 0.0000 +165.0000 -0.6800 0.2300 0.0000 +170.0000 -0.8500 0.1400 0.0000 +175.0000 -0.6600 0.0550 0.0000 +180.0000 0.0000 0.0250 0.0000 + +Reynolds Number: 7e5 +BV Dyn. Stall Model - Positive Stall AOA (deg): 6.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -6.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.32 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.32 +AOA (deg) CL CD Cm25 +-180.0000 0.0000 0.0250 0.0000 +-175.0000 0.6600 0.0550 0.0000 +-170.0000 0.8500 0.1400 0.0000 +-165.0000 0.6800 0.2300 0.0000 +-160.0000 0.6350 0.3200 0.0000 +-155.0000 0.6700 0.4200 0.0000 +-150.0000 0.7700 0.5750 0.0000 +-145.0000 0.9000 0.7550 0.0000 +-140.0000 0.9800 0.9250 0.0000 +-135.0000 0.9300 1.0850 0.0000 +-130.0000 0.8500 1.2250 0.0000 +-125.0000 0.7600 1.3500 0.0000 +-120.0000 0.6700 1.4650 0.0000 +-115.0000 0.5750 1.5550 0.0000 +-110.0000 0.4500 1.6350 0.0000 +-105.0000 0.3200 1.7000 0.0000 +-100.0000 0.1850 1.7500 0.0000 +-95.0000 0.0500 1.7800 0.0000 +-90.0000 -0.0900 1.8000 0.0000 +-85.0000 -0.2300 1.8000 0.0000 +-80.0000 -0.3650 1.7800 0.0000 +-75.0000 -0.5000 1.7350 0.0000 +-70.0000 -0.6300 1.6650 0.0000 +-65.0000 -0.7600 1.5750 0.0000 +-60.0000 -0.8750 1.4700 0.0000 +-55.0000 -0.9550 1.3450 0.0000 +-50.0000 -1.0200 1.2150 0.0000 +-45.0000 -1.0500 1.0750 0.0000 +-40.0000 -1.0350 0.9200 0.0000 +-35.0000 -0.9800 0.7450 0.0000 +-30.0000 -0.8550 0.5700 0.0000 +-27.0000 -0.9473 0.4600 0.0000 +-26.0000 -0.8838 0.4320 0.0000 +-25.0000 -0.8353 0.4050 0.0000 +-24.0000 -0.7961 0.3790 0.0000 +-23.0000 -0.7593 0.3540 0.0000 +-22.0000 -0.7298 0.3290 0.0000 +-21.0000 -0.7097 0.3050 0.0000 +-20.0000 -0.6990 0.2820 0.0000 +-19.0000 -0.7041 0.2600 0.0000 +-18.0000 -0.7305 0.2380 0.0000 +-17.0000 -0.7799 0.1340 0.0000 +-16.0000 -0.8401 0.0297 0.0000 +-15.0000 -0.9119 0.0269 0.0000 +-14.0000 -0.9801 0.0244 0.0000 +-13.0000 -1.0302 0.0221 0.0000 +-12.0000 -1.0508 0.0200 0.0000 +-11.0000 -1.0363 0.0182 0.0000 +-10.0000 -0.9937 0.0164 0.0000 +-9.0000 -0.9260 0.0149 0.0000 +-8.0000 -0.8442 0.0135 0.0000 +-7.0000 -0.7483 0.0122 0.0000 +-6.0000 -0.6600 0.0108 0.0000 +-5.0000 -0.5500 0.0098 0.0000 +-4.0000 -0.4400 0.0089 0.0000 +-3.0000 -0.3300 0.0083 0.0000 +-2.0000 -0.2200 0.0080 0.0000 +-1.0000 -0.1100 0.0078 0.0000 +0.0000 0.0000 0.0077 0.0000 +1.0000 0.1100 0.0078 0.0000 +2.0000 0.2200 0.0080 0.0000 +3.0000 0.3300 0.0083 0.0000 +4.0000 0.4400 0.0089 0.0000 +5.0000 0.5500 0.0098 0.0000 +6.0000 0.6600 0.0108 0.0000 +7.0000 0.7483 0.0122 0.0000 +8.0000 0.8442 0.0135 0.0000 +9.0000 0.9260 0.0149 0.0000 +10.0000 0.9937 0.0164 0.0000 +11.0000 1.0363 0.0182 0.0000 +12.0000 1.0508 0.0200 0.0000 +13.0000 1.0302 0.0221 0.0000 +14.0000 0.9801 0.0244 0.0000 +15.0000 0.9119 0.0269 0.0000 +16.0000 0.8401 0.0297 0.0000 +17.0000 0.7799 0.1340 0.0000 +18.0000 0.7305 0.2380 0.0000 +19.0000 0.7041 0.2600 0.0000 +20.0000 0.6990 0.2820 0.0000 +21.0000 0.7097 0.3050 0.0000 +22.0000 0.7298 0.3290 0.0000 +23.0000 0.7593 0.3540 0.0000 +24.0000 0.7961 0.3790 0.0000 +25.0000 0.8353 0.4050 0.0000 +26.0000 0.8838 0.4320 0.0000 +27.0000 0.9473 0.4600 0.0000 +30.0000 0.8550 0.5700 0.0000 +35.0000 0.9800 0.7450 0.0000 +40.0000 1.0350 0.9200 0.0000 +45.0000 1.0500 1.0750 0.0000 +50.0000 1.0200 1.2150 0.0000 +55.0000 0.9550 1.3450 0.0000 +60.0000 0.8750 1.4700 0.0000 +65.0000 0.7600 1.5750 0.0000 +70.0000 0.6300 1.6650 0.0000 +75.0000 0.5000 1.7350 0.0000 +80.0000 0.3650 1.7800 0.0000 +85.0000 0.2300 1.8000 0.0000 +90.0000 0.0900 1.8000 0.0000 +95.0000 -0.0500 1.7800 0.0000 +100.0000 -0.1850 1.7500 0.0000 +105.0000 -0.3200 1.7000 0.0000 +110.0000 -0.4500 1.6350 0.0000 +115.0000 -0.5750 1.5550 0.0000 +120.0000 -0.6700 1.4650 0.0000 +125.0000 -0.7600 1.3500 0.0000 +130.0000 -0.8500 1.2250 0.0000 +135.0000 -0.9300 1.0850 0.0000 +140.0000 -0.9800 0.9250 0.0000 +145.0000 -0.9000 0.7550 0.0000 +150.0000 -0.7700 0.5750 0.0000 +155.0000 -0.6700 0.4200 0.0000 +160.0000 -0.6350 0.3200 0.0000 +165.0000 -0.6800 0.2300 0.0000 +170.0000 -0.8500 0.1400 0.0000 +175.0000 -0.6600 0.0550 0.0000 +180.0000 0.0000 0.0250 0.0000 + +Reynolds Number: 1e6 +BV Dyn. Stall Model - Positive Stall AOA (deg): 7.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -7.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.32 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.32 +AOA (deg) CL CD Cm25 +-180.0000 0.0000 0.0250 0.0000 +-175.0000 0.6600 0.0550 0.0000 +-170.0000 0.8500 0.1400 0.0000 +-165.0000 0.6800 0.2300 0.0000 +-160.0000 0.6350 0.3200 0.0000 +-155.0000 0.6700 0.4200 0.0000 +-150.0000 0.7700 0.5750 0.0000 +-145.0000 0.9000 0.7550 0.0000 +-140.0000 0.9800 0.9250 0.0000 +-135.0000 0.9300 1.0850 0.0000 +-130.0000 0.8500 1.2250 0.0000 +-125.0000 0.7600 1.3500 0.0000 +-120.0000 0.6700 1.4650 0.0000 +-115.0000 0.5750 1.5550 0.0000 +-110.0000 0.4500 1.6350 0.0000 +-105.0000 0.3200 1.7000 0.0000 +-100.0000 0.1850 1.7500 0.0000 +-95.0000 0.0500 1.7800 0.0000 +-90.0000 -0.0900 1.8000 0.0000 +-85.0000 -0.2300 1.8000 0.0000 +-80.0000 -0.3650 1.7800 0.0000 +-75.0000 -0.5000 1.7350 0.0000 +-70.0000 -0.6300 1.6650 0.0000 +-65.0000 -0.7600 1.5750 0.0000 +-60.0000 -0.8750 1.4700 0.0000 +-55.0000 -0.9550 1.3450 0.0000 +-50.0000 -1.0200 1.2150 0.0000 +-45.0000 -1.0500 1.0750 0.0000 +-40.0000 -1.0350 0.9200 0.0000 +-35.0000 -0.9800 0.7450 0.0000 +-30.0000 -0.8550 0.5700 0.0000 +-27.0000 -0.9912 0.4600 0.0000 +-26.0000 -0.9406 0.4320 0.0000 +-25.0000 -0.9023 0.4050 0.0000 +-24.0000 -0.8668 0.3790 0.0000 +-23.0000 -0.8408 0.3540 0.0000 +-22.0000 -0.8189 0.3290 0.0000 +-21.0000 -0.8063 0.3050 0.0000 +-20.0000 -0.8089 0.2820 0.0000 +-19.0000 -0.8226 0.2600 0.0000 +-18.0000 -0.8566 0.1450 0.0000 +-17.0000 -0.8996 0.0303 0.0000 +-16.0000 -0.9567 0.0275 0.0000 +-15.0000 -1.0145 0.0249 0.0000 +-14.0000 -1.0656 0.0225 0.0000 +-13.0000 -1.0957 0.0205 0.0000 +-12.0000 -1.0971 0.0186 0.0000 +-11.0000 -1.0686 0.0168 0.0000 +-10.0000 -1.0141 0.0152 0.0000 +-9.0000 -0.9387 0.0138 0.0000 +-8.0000 -0.8504 0.0126 0.0000 +-7.0000 -0.7700 0.0111 0.0000 +-6.0000 -0.6600 0.0101 0.0000 +-5.0000 -0.5500 0.0091 0.0000 +-4.0000 -0.4400 0.0083 0.0000 +-3.0000 -0.3300 0.0079 0.0000 +-2.0000 -0.2200 0.0076 0.0000 +-1.0000 -0.1100 0.0075 0.0000 +0.0000 0.0000 0.0074 0.0000 +1.0000 0.1100 0.0075 0.0000 +2.0000 0.2200 0.0076 0.0000 +3.0000 0.3300 0.0079 0.0000 +4.0000 0.4400 0.0083 0.0000 +5.0000 0.5500 0.0091 0.0000 +6.0000 0.6600 0.0101 0.0000 +7.0000 0.7700 0.0111 0.0000 +8.0000 0.8504 0.0126 0.0000 +9.0000 0.9387 0.0138 0.0000 +10.0000 1.0141 0.0152 0.0000 +11.0000 1.0686 0.0168 0.0000 +12.0000 1.0971 0.0186 0.0000 +13.0000 1.0957 0.0205 0.0000 +14.0000 1.0656 0.0225 0.0000 +15.0000 1.0145 0.0249 0.0000 +16.0000 0.9567 0.0275 0.0000 +17.0000 0.8996 0.0303 0.0000 +18.0000 0.8566 0.1450 0.0000 +19.0000 0.8226 0.2600 0.0000 +20.0000 0.8089 0.2820 0.0000 +21.0000 0.8063 0.3050 0.0000 +22.0000 0.8189 0.3290 0.0000 +23.0000 0.8408 0.3540 0.0000 +24.0000 0.8668 0.3790 0.0000 +25.0000 0.9023 0.4050 0.0000 +26.0000 0.9406 0.4320 0.0000 +27.0000 0.9912 0.4600 0.0000 +30.0000 0.8550 0.5700 0.0000 +35.0000 0.9800 0.7450 0.0000 +40.0000 1.0350 0.9200 0.0000 +45.0000 1.0500 1.0750 0.0000 +50.0000 1.0200 1.2150 0.0000 +55.0000 0.9550 1.3450 0.0000 +60.0000 0.8750 1.4700 0.0000 +65.0000 0.7600 1.5750 0.0000 +70.0000 0.6300 1.6650 0.0000 +75.0000 0.5000 1.7350 0.0000 +80.0000 0.3650 1.7800 0.0000 +85.0000 0.2300 1.8000 0.0000 +90.0000 0.0900 1.8000 0.0000 +95.0000 -0.0500 1.7800 0.0000 +100.0000 -0.1850 1.7500 0.0000 +105.0000 -0.3200 1.7000 0.0000 +110.0000 -0.4500 1.6350 0.0000 +115.0000 -0.5750 1.5550 0.0000 +120.0000 -0.6700 1.4650 0.0000 +125.0000 -0.7600 1.3500 0.0000 +130.0000 -0.8500 1.2250 0.0000 +135.0000 -0.9300 1.0850 0.0000 +140.0000 -0.9800 0.9250 0.0000 +145.0000 -0.9000 0.7550 0.0000 +150.0000 -0.7700 0.5750 0.0000 +155.0000 -0.6700 0.4200 0.0000 +160.0000 -0.6350 0.3200 0.0000 +165.0000 -0.6800 0.2300 0.0000 +170.0000 -0.8500 0.1400 0.0000 +175.0000 -0.6600 0.0550 0.0000 +180.0000 0.0000 0.0250 0.0000 + +Reynolds Number: 2e6 +BV Dyn. Stall Model - Positive Stall AOA (deg): 8.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -8.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.43 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.43 +AOA (deg) CL CD Cm25 +-180.0000 0.0000 0.0250 0.0000 +-175.0000 0.6600 0.0550 0.0000 +-170.0000 0.8500 0.1400 0.0000 +-165.0000 0.6800 0.2300 0.0000 +-160.0000 0.6350 0.3200 0.0000 +-155.0000 0.6700 0.4200 0.0000 +-150.0000 0.7700 0.5750 0.0000 +-145.0000 0.9000 0.7550 0.0000 +-140.0000 0.9800 0.9250 0.0000 +-135.0000 0.9300 1.0850 0.0000 +-130.0000 0.8500 1.2250 0.0000 +-125.0000 0.7600 1.3500 0.0000 +-120.0000 0.6700 1.4650 0.0000 +-115.0000 0.5750 1.5550 0.0000 +-110.0000 0.4500 1.6350 0.0000 +-105.0000 0.3200 1.7000 0.0000 +-100.0000 0.1850 1.7500 0.0000 +-95.0000 0.0500 1.7800 0.0000 +-90.0000 -0.0900 1.8000 0.0000 +-85.0000 -0.2300 1.8000 0.0000 +-80.0000 -0.3650 1.7800 0.0000 +-75.0000 -0.5000 1.7350 0.0000 +-70.0000 -0.6300 1.6650 0.0000 +-65.0000 -0.7600 1.5750 0.0000 +-60.0000 -0.8750 1.4700 0.0000 +-55.0000 -0.9550 1.3450 0.0000 +-50.0000 -1.0200 1.2150 0.0000 +-45.0000 -1.0500 1.0750 0.0000 +-40.0000 -1.0350 0.9200 0.0000 +-35.0000 -0.9800 0.7450 0.0000 +-30.0000 -0.8550 0.5700 0.0000 +-27.0000 -1.0810 0.4600 0.0000 +-26.0000 -1.0591 0.4320 0.0000 +-25.0000 -1.0317 0.4050 0.0000 +-24.0000 -1.0078 0.3790 0.0000 +-23.0000 -0.9910 0.3540 0.0000 +-22.0000 -0.9827 0.3290 0.0000 +-21.0000 -0.9837 0.3050 0.0000 +-20.0000 -0.9954 0.2820 0.0000 +-19.0000 -1.0173 0.1550 0.0000 +-18.0000 -1.0510 0.0288 0.0000 +-17.0000 -1.0921 0.0261 0.0000 +-16.0000 -1.1356 0.0237 0.0000 +-15.0000 -1.1744 0.0215 0.0000 +-14.0000 -1.1962 0.0195 0.0000 +-13.0000 -1.1948 0.0177 0.0000 +-12.0000 -1.1667 0.0161 0.0000 +-11.0000 -1.1138 0.0146 0.0000 +-10.0000 -1.0433 0.0133 0.0000 +-9.0000 -0.9574 0.0121 0.0000 +-8.0000 -0.8800 0.0108 0.0000 +-7.0000 -0.7700 0.0098 0.0000 +-6.0000 -0.6600 0.0090 0.0000 +-5.0000 -0.5500 0.0083 0.0000 +-4.0000 -0.4400 0.0078 0.0000 +-3.0000 -0.3300 0.0075 0.0000 +-2.0000 -0.2200 0.0072 0.0000 +-1.0000 -0.1100 0.0071 0.0000 +0.0000 0.0000 0.0070 0.0000 +1.0000 0.1100 0.0071 0.0000 +2.0000 0.2200 0.0072 0.0000 +3.0000 0.3300 0.0075 0.0000 +4.0000 0.4400 0.0078 0.0000 +5.0000 0.5500 0.0083 0.0000 +6.0000 0.6600 0.0090 0.0000 +7.0000 0.7700 0.0098 0.0000 +8.0000 0.8800 0.0108 0.0000 +9.0000 0.9574 0.0121 0.0000 +10.0000 1.0433 0.0133 0.0000 +11.0000 1.1138 0.0146 0.0000 +12.0000 1.1667 0.0161 0.0000 +13.0000 1.1948 0.0177 0.0000 +14.0000 1.1962 0.0195 0.0000 +15.0000 1.1744 0.0215 0.0000 +16.0000 1.1356 0.0237 0.0000 +17.0000 1.0921 0.0261 0.0000 +18.0000 1.0510 0.0288 0.0000 +19.0000 1.0173 0.1550 0.0000 +20.0000 0.9954 0.2820 0.0000 +21.0000 0.9837 0.3050 0.0000 +22.0000 0.9827 0.3290 0.0000 +23.0000 0.9910 0.3540 0.0000 +24.0000 1.0078 0.3790 0.0000 +25.0000 1.0317 0.4050 0.0000 +26.0000 1.0591 0.4320 0.0000 +27.0000 1.0810 0.4600 0.0000 +30.0000 0.8550 0.5700 0.0000 +35.0000 0.9800 0.7450 0.0000 +40.0000 1.0350 0.9200 0.0000 +45.0000 1.0500 1.0750 0.0000 +50.0000 1.0200 1.2150 0.0000 +55.0000 0.9550 1.3450 0.0000 +60.0000 0.8750 1.4700 0.0000 +65.0000 0.7600 1.5750 0.0000 +70.0000 0.6300 1.6650 0.0000 +75.0000 0.5000 1.7350 0.0000 +80.0000 0.3650 1.7800 0.0000 +85.0000 0.2300 1.8000 0.0000 +90.0000 0.0900 1.8000 0.0000 +95.0000 -0.0500 1.7800 0.0000 +100.0000 -0.1850 1.7500 0.0000 +105.0000 -0.3200 1.7000 0.0000 +110.0000 -0.4500 1.6350 0.0000 +115.0000 -0.5750 1.5550 0.0000 +120.0000 -0.6700 1.4650 0.0000 +125.0000 -0.7600 1.3500 0.0000 +130.0000 -0.8500 1.2250 0.0000 +135.0000 -0.9300 1.0850 0.0000 +140.0000 -0.9800 0.9250 0.0000 +145.0000 -0.9000 0.7550 0.0000 +150.0000 -0.7700 0.5750 0.0000 +155.0000 -0.6700 0.4200 0.0000 +160.0000 -0.6350 0.3200 0.0000 +165.0000 -0.6800 0.2300 0.0000 +170.0000 -0.8500 0.1400 0.0000 +175.0000 -0.6600 0.0550 0.0000 +180.0000 0.0000 0.0250 0.0000 + +Reynolds Number: 5e6 +BV Dyn. Stall Model - Positive Stall AOA (deg): 9.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -9.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.65 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.65 +AOA (deg) CL CD Cm25 +-180.0000 0.0000 0.0250 0.0000 +-175.0000 0.6600 0.0550 0.0000 +-170.0000 0.8500 0.1400 0.0000 +-165.0000 0.6800 0.2300 0.0000 +-160.0000 0.6350 0.3200 0.0000 +-155.0000 0.6700 0.4200 0.0000 +-150.0000 0.7700 0.5750 0.0000 +-145.0000 0.9000 0.7550 0.0000 +-140.0000 0.9800 0.9250 0.0000 +-135.0000 0.9300 1.0850 0.0000 +-130.0000 0.8500 1.2250 0.0000 +-125.0000 0.7600 1.3500 0.0000 +-120.0000 0.6700 1.4650 0.0000 +-115.0000 0.5750 1.5550 0.0000 +-110.0000 0.4500 1.6350 0.0000 +-105.0000 0.3200 1.7000 0.0000 +-100.0000 0.1850 1.7500 0.0000 +-95.0000 0.0500 1.7800 0.0000 +-90.0000 -0.0900 1.8000 0.0000 +-85.0000 -0.2300 1.8000 0.0000 +-80.0000 -0.3650 1.7800 0.0000 +-75.0000 -0.5000 1.7350 0.0000 +-70.0000 -0.6300 1.6650 0.0000 +-65.0000 -0.7600 1.5750 0.0000 +-60.0000 -0.8750 1.4700 0.0000 +-55.0000 -0.9550 1.3450 0.0000 +-50.0000 -1.0200 1.2150 0.0000 +-45.0000 -1.0500 1.0750 0.0000 +-40.0000 -1.0350 0.9200 0.0000 +-35.0000 -0.9800 0.7450 0.0000 +-30.0000 -0.8550 0.5700 0.0000 +-27.0000 -1.1397 0.4600 0.0000 +-26.0000 -1.1268 0.4320 0.0000 +-25.0000 -1.1322 0.4050 0.0000 +-24.0000 -1.1563 0.3790 0.0000 +-23.0000 -1.1611 0.3540 0.0000 +-22.0000 -1.1647 0.3290 0.0000 +-21.0000 -1.1771 0.3050 0.0000 +-20.0000 -1.1965 0.1660 0.0000 +-19.0000 -1.2242 0.0265 0.0000 +-18.0000 -1.2576 0.0240 0.0000 +-17.0000 -1.2917 0.0218 0.0000 +-16.0000 -1.3186 0.0198 0.0000 +-15.0000 -1.3298 0.0180 0.0000 +-14.0000 -1.3187 0.0164 0.0000 +-13.0000 -1.2847 0.0149 0.0000 +-12.0000 -1.2290 0.0136 0.0000 +-11.0000 -1.1553 0.0124 0.0000 +-10.0000 -1.0685 0.0113 0.0000 +-9.0000 -0.9900 0.0102 0.0000 +-8.0000 -0.8800 0.0095 0.0000 +-7.0000 -0.7700 0.0089 0.0000 +-6.0000 -0.6600 0.0084 0.0000 +-5.0000 -0.5500 0.0080 0.0000 +-4.0000 -0.4400 0.0075 0.0000 +-3.0000 -0.3300 0.0073 0.0000 +-2.0000 -0.2200 0.0070 0.0000 +-1.0000 -0.1100 0.0069 0.0000 +0.0000 0.0000 0.0068 0.0000 +1.0000 0.1100 0.0069 0.0000 +2.0000 0.2200 0.0070 0.0000 +3.0000 0.3300 0.0073 0.0000 +4.0000 0.4400 0.0075 0.0000 +5.0000 0.5500 0.0080 0.0000 +6.0000 0.6600 0.0084 0.0000 +7.0000 0.7700 0.0089 0.0000 +8.0000 0.8800 0.0095 0.0000 +9.0000 0.9900 0.0102 0.0000 +10.0000 1.0685 0.0113 0.0000 +11.0000 1.1553 0.0124 0.0000 +12.0000 1.2290 0.0136 0.0000 +13.0000 1.2847 0.0149 0.0000 +14.0000 1.3187 0.0164 0.0000 +15.0000 1.3298 0.0180 0.0000 +16.0000 1.3186 0.0198 0.0000 +17.0000 1.2917 0.0218 0.0000 +18.0000 1.2576 0.0240 0.0000 +19.0000 1.2242 0.0265 0.0000 +20.0000 1.1965 0.1660 0.0000 +21.0000 1.1771 0.3050 0.0000 +22.0000 1.1647 0.3290 0.0000 +23.0000 1.1611 0.3540 0.0000 +24.0000 1.1563 0.3790 0.0000 +25.0000 1.1322 0.4050 0.0000 +26.0000 1.1268 0.4320 0.0000 +27.0000 1.1397 0.4600 0.0000 +30.0000 0.8550 0.5700 0.0000 +35.0000 0.9800 0.7450 0.0000 +40.0000 1.0350 0.9200 0.0000 +45.0000 1.0500 1.0750 0.0000 +50.0000 1.0200 1.2150 0.0000 +55.0000 0.9550 1.3450 0.0000 +60.0000 0.8750 1.4700 0.0000 +65.0000 0.7600 1.5750 0.0000 +70.0000 0.6300 1.6650 0.0000 +75.0000 0.5000 1.7350 0.0000 +80.0000 0.3650 1.7800 0.0000 +85.0000 0.2300 1.8000 0.0000 +90.0000 0.0900 1.8000 0.0000 +95.0000 -0.0500 1.7800 0.0000 +100.0000 -0.1850 1.7500 0.0000 +105.0000 -0.3200 1.7000 0.0000 +110.0000 -0.4500 1.6350 0.0000 +115.0000 -0.5750 1.5550 0.0000 +120.0000 -0.6700 1.4650 0.0000 +125.0000 -0.7600 1.3500 0.0000 +130.0000 -0.8500 1.2250 0.0000 +135.0000 -0.9300 1.0850 0.0000 +140.0000 -0.9800 0.9250 0.0000 +145.0000 -0.9000 0.7550 0.0000 +150.0000 -0.7700 0.5750 0.0000 +155.0000 -0.6700 0.4200 0.0000 +160.0000 -0.6350 0.3200 0.0000 +165.0000 -0.6800 0.2300 0.0000 +170.0000 -0.8500 0.1400 0.0000 +175.0000 -0.6600 0.0550 0.0000 +180.0000 0.0000 0.0250 0.0000 + +Reynolds Number: 1e7 +BV Dyn. Stall Model - Positive Stall AOA (deg): 10.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -10.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.65 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.65 +AOA (deg) CL CD Cm25 +-180.0000 0.0000 0.0250 0.0000 +-175.0000 0.6600 0.0550 0.0000 +-170.0000 0.8500 0.1400 0.0000 +-165.0000 0.6800 0.2300 0.0000 +-160.0000 0.6350 0.3200 0.0000 +-155.0000 0.6700 0.4200 0.0000 +-150.0000 0.7700 0.5750 0.0000 +-145.0000 0.9000 0.7550 0.0000 +-140.0000 0.9800 0.9250 0.0000 +-135.0000 0.9300 1.0850 0.0000 +-130.0000 0.8500 1.2250 0.0000 +-125.0000 0.7600 1.3500 0.0000 +-120.0000 0.6700 1.4650 0.0000 +-115.0000 0.5750 1.5550 0.0000 +-110.0000 0.4500 1.6350 0.0000 +-105.0000 0.3200 1.7000 0.0000 +-100.0000 0.1850 1.7500 0.0000 +-95.0000 0.0500 1.7800 0.0000 +-90.0000 -0.0900 1.8000 0.0000 +-85.0000 -0.2300 1.8000 0.0000 +-80.0000 -0.3650 1.7800 0.0000 +-75.0000 -0.5000 1.7350 0.0000 +-70.0000 -0.6300 1.6650 0.0000 +-65.0000 -0.7600 1.5750 0.0000 +-60.0000 -0.8750 1.4700 0.0000 +-55.0000 -0.9550 1.3450 0.0000 +-50.0000 -1.0200 1.2150 0.0000 +-45.0000 -1.0500 1.0750 0.0000 +-40.0000 -1.0350 0.9200 0.0000 +-35.0000 -0.9800 0.7450 0.0000 +-30.0000 -0.8550 0.5700 0.0000 +-27.0000 -1.1519 0.4600 0.0000 +-26.0000 -1.1374 0.4320 0.0000 +-25.0000 -1.1380 0.4050 0.0000 +-24.0000 -1.1538 0.3790 0.0000 +-23.0000 -1.1981 0.3540 0.0000 +-22.0000 -1.2767 0.3290 0.0000 +-21.0000 -1.3077 0.1770 0.0000 +-20.0000 -1.3325 0.0257 0.0000 +-19.0000 -1.3608 0.0234 0.0000 +-18.0000 -1.3897 0.0213 0.0000 +-17.0000 -1.4136 0.0194 0.0000 +-16.0000 -1.4233 0.0176 0.0000 +-15.0000 -1.4136 0.0161 0.0000 +-14.0000 -1.3825 0.0147 0.0000 +-13.0000 -1.3300 0.0134 0.0000 +-12.0000 -1.2591 0.0123 0.0000 +-11.0000 -1.1749 0.0114 0.0000 +-10.0000 -1.1000 0.0103 0.0000 +-9.0000 -0.9900 0.0096 0.0000 +-8.0000 -0.8800 0.0090 0.0000 +-7.0000 -0.7700 0.0086 0.0000 +-6.0000 -0.6600 0.0081 0.0000 +-5.0000 -0.5500 0.0077 0.0000 +-4.0000 -0.4400 0.0074 0.0000 +-3.0000 -0.3300 0.0071 0.0000 +-2.0000 -0.2200 0.0069 0.0000 +-1.0000 -0.1100 0.0068 0.0000 +0.0000 0.0000 0.0068 0.0000 +1.0000 0.1100 0.0068 0.0000 +2.0000 0.2200 0.0069 0.0000 +3.0000 0.3300 0.0071 0.0000 +4.0000 0.4400 0.0074 0.0000 +5.0000 0.5500 0.0077 0.0000 +6.0000 0.6600 0.0081 0.0000 +7.0000 0.7700 0.0086 0.0000 +8.0000 0.8800 0.0090 0.0000 +9.0000 0.9900 0.0096 0.0000 +10.0000 1.1000 0.0103 0.0000 +11.0000 1.1749 0.0114 0.0000 +12.0000 1.2591 0.0123 0.0000 +13.0000 1.3300 0.0134 0.0000 +14.0000 1.3825 0.0147 0.0000 +15.0000 1.4136 0.0161 0.0000 +16.0000 1.4233 0.0176 0.0000 +17.0000 1.4136 0.0194 0.0000 +18.0000 1.3897 0.0213 0.0000 +19.0000 1.3608 0.0234 0.0000 +20.0000 1.3325 0.0257 0.0000 +21.0000 1.3077 0.1770 0.0000 +22.0000 1.2767 0.3290 0.0000 +23.0000 1.1981 0.3540 0.0000 +24.0000 1.1538 0.3790 0.0000 +25.0000 1.1380 0.4050 0.0000 +26.0000 1.1374 0.4320 0.0000 +27.0000 1.1519 0.4600 0.0000 +30.0000 0.8550 0.5700 0.0000 +35.0000 0.9800 0.7450 0.0000 +40.0000 1.0350 0.9200 0.0000 +45.0000 1.0500 1.0750 0.0000 +50.0000 1.0200 1.2150 0.0000 +55.0000 0.9550 1.3450 0.0000 +60.0000 0.8750 1.4700 0.0000 +65.0000 0.7600 1.5750 0.0000 +70.0000 0.6300 1.6650 0.0000 +75.0000 0.5000 1.7350 0.0000 +80.0000 0.3650 1.7800 0.0000 +85.0000 0.2300 1.8000 0.0000 +90.0000 0.0900 1.8000 0.0000 +95.0000 -0.0500 1.7800 0.0000 +100.0000 -0.1850 1.7500 0.0000 +105.0000 -0.3200 1.7000 0.0000 +110.0000 -0.4500 1.6350 0.0000 +115.0000 -0.5750 1.5550 0.0000 +120.0000 -0.6700 1.4650 0.0000 +125.0000 -0.7600 1.3500 0.0000 +130.0000 -0.8500 1.2250 0.0000 +135.0000 -0.9300 1.0850 0.0000 +140.0000 -0.9800 0.9250 0.0000 +145.0000 -0.9000 0.7550 0.0000 +150.0000 -0.7700 0.5750 0.0000 +155.0000 -0.6700 0.4200 0.0000 +160.0000 -0.6350 0.3200 0.0000 +165.0000 -0.6800 0.2300 0.0000 +170.0000 -0.8500 0.1400 0.0000 +175.0000 -0.6600 0.0550 0.0000 +180.0000 0.0000 0.0250 0.0000 diff --git a/examples/Optimization/airfoils/NACA_0015_RE3E5.dat b/examples/Optimization/airfoils/NACA_0015_RE3E5.dat new file mode 100644 index 00000000..9056804e --- /dev/null +++ b/examples/Optimization/airfoils/NACA_0015_RE3E5.dat @@ -0,0 +1,130 @@ +Title: NACA0015 +Thickness to Chord Ratio: 0.15 +Zero Lift AOA (deg): 0.0 +Reverse Camber Direction: 0 +Reynolds Number: 3.6e5 +BV Dyn. Stall Model - Positive Stall AOA (deg): 6.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -6.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.21 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.21 +skipline +AOA (deg) CL CD Cm25 +-180.0000 0.0000 0.0250 0.0000 +-175.0000 0.6600 0.0550 0.0000 +-170.0000 0.8500 0.1400 0.0000 +-165.0000 0.6800 0.2300 0.0000 +-160.0000 0.6350 0.3200 0.0000 +-155.0000 0.6700 0.4200 0.0000 +-150.0000 0.7700 0.5750 0.0000 +-145.0000 0.9000 0.7550 0.0000 +-140.0000 0.9800 0.9250 0.0000 +-135.0000 0.9300 1.0850 0.0000 +-130.0000 0.8500 1.2250 0.0000 +-125.0000 0.7600 1.3500 0.0000 +-120.0000 0.6700 1.4650 0.0000 +-115.0000 0.5750 1.5550 0.0000 +-110.0000 0.4500 1.6350 0.0000 +-105.0000 0.3200 1.7000 0.0000 +-100.0000 0.1850 1.7500 0.0000 +-95.0000 0.0500 1.7800 0.0000 +-90.0000 -0.0900 1.8000 0.0000 +-85.0000 -0.2300 1.8000 0.0000 +-80.0000 -0.3650 1.7800 0.0000 +-75.0000 -0.5000 1.7350 0.0000 +-70.0000 -0.6300 1.6650 0.0000 +-65.0000 -0.7600 1.5750 0.0000 +-60.0000 -0.8750 1.4700 0.0000 +-55.0000 -0.9550 1.3450 0.0000 +-50.0000 -1.0200 1.2150 0.0000 +-45.0000 -1.0500 1.0750 0.0000 +-40.0000 -1.0350 0.9200 0.0000 +-35.0000 -0.9800 0.7450 0.0000 +-30.0000 -0.8550 0.5700 0.0000 +-27.0000 -0.8788 0.4600 0.0000 +-26.0000 -0.8055 0.4320 0.0000 +-25.0000 -0.7511 0.4050 0.0000 +-24.0000 -0.7015 0.3790 0.0000 +-23.0000 -0.6528 0.3540 0.0000 +-22.0000 -0.6045 0.3290 0.0000 +-21.0000 -0.5616 0.3050 0.0000 +-20.0000 -0.5247 0.2820 0.0000 +-19.0000 -0.4908 0.2600 0.0000 +-18.0000 -0.4782 0.2380 0.0000 +-17.0000 -0.4851 0.2170 0.0000 +-16.0000 -0.5384 0.1240 0.0000 +-15.0000 -0.6350 0.0312 0.0000 +-14.0000 -0.7483 0.0283 0.0000 +-13.0000 -0.8562 0.0257 0.0000 +-12.0000 -0.9285 0.0233 0.0000 +-11.0000 -0.9572 0.0211 0.0000 +-10.0000 -0.9440 0.0191 0.0000 +-9.0000 -0.8946 0.0173 0.0000 +-8.0000 -0.8240 0.0157 0.0000 +-7.0000 -0.7390 0.0143 0.0000 +-6.0000 -0.6600 0.0126 0.0000 +-5.0000 -0.5500 0.0114 0.0000 +-4.0000 -0.4400 0.0105 0.0000 +-3.0000 -0.3300 0.0098 0.0000 +-2.0000 -0.2200 0.0094 0.0000 +-1.0000 -0.1100 0.0092 0.0000 +0.0000 0.0000 0.0091 0.0000 +1.0000 0.1100 0.0092 0.0000 +2.0000 0.2200 0.0094 0.0000 +3.0000 0.3300 0.0098 0.0000 +4.0000 0.4400 0.0105 0.0000 +5.0000 0.5500 0.0114 0.0000 +6.0000 0.6600 0.0126 0.0000 +7.0000 0.7390 0.0143 0.0000 +8.0000 0.8240 0.0157 0.0000 +9.0000 0.8946 0.0173 0.0000 +10.0000 0.9440 0.0191 0.0000 +11.0000 0.9572 0.0211 0.0000 +12.0000 0.9285 0.0233 0.0000 +13.0000 0.8562 0.0257 0.0000 +14.0000 0.7483 0.0283 0.0000 +15.0000 0.6350 0.0312 0.0000 +16.0000 0.5384 0.1240 0.0000 +17.0000 0.4851 0.2170 0.0000 +18.0000 0.4782 0.2380 0.0000 +19.0000 0.4908 0.2600 0.0000 +20.0000 0.5247 0.2820 0.0000 +21.0000 0.5616 0.3050 0.0000 +22.0000 0.6045 0.3290 0.0000 +23.0000 0.6528 0.3540 0.0000 +24.0000 0.7015 0.3790 0.0000 +25.0000 0.7511 0.4050 0.0000 +26.0000 0.8055 0.4320 0.0000 +27.0000 0.8788 0.4600 0.0000 +30.0000 0.8550 0.5700 0.0000 +35.0000 0.9800 0.7450 0.0000 +40.0000 1.0350 0.9200 0.0000 +45.0000 1.0500 1.0750 0.0000 +50.0000 1.0200 1.2150 0.0000 +55.0000 0.9550 1.3450 0.0000 +60.0000 0.8750 1.4700 0.0000 +65.0000 0.7600 1.5750 0.0000 +70.0000 0.6300 1.6650 0.0000 +75.0000 0.5000 1.7350 0.0000 +80.0000 0.3650 1.7800 0.0000 +85.0000 0.2300 1.8000 0.0000 +90.0000 0.0900 1.8000 0.0000 +95.0000 -0.0500 1.7800 0.0000 +100.0000 -0.1850 1.7500 0.0000 +105.0000 -0.3200 1.7000 0.0000 +110.0000 -0.4500 1.6350 0.0000 +115.0000 -0.5750 1.5550 0.0000 +120.0000 -0.6700 1.4650 0.0000 +125.0000 -0.7600 1.3500 0.0000 +130.0000 -0.8500 1.2250 0.0000 +135.0000 -0.9300 1.0850 0.0000 +140.0000 -0.9800 0.9250 0.0000 +145.0000 -0.9000 0.7550 0.0000 +150.0000 -0.7700 0.5750 0.0000 +155.0000 -0.6700 0.4200 0.0000 +160.0000 -0.6350 0.3200 0.0000 +165.0000 -0.6800 0.2300 0.0000 +170.0000 -0.8500 0.1400 0.0000 +175.0000 -0.6600 0.0550 0.0000 +180.0000 0.0000 0.0250 0.0000 +EOT diff --git a/examples/helical_riverine/airfoils/NACA_0018_AllRe.dat b/examples/Optimization/airfoils/NACA_0018_AllRe.dat similarity index 100% rename from examples/helical_riverine/airfoils/NACA_0018_AllRe.dat rename to examples/Optimization/airfoils/NACA_0018_AllRe.dat diff --git a/examples/Optimization/airfoils/NACA_0018_Coords.txt b/examples/Optimization/airfoils/NACA_0018_Coords.txt new file mode 100644 index 00000000..39bdb98e --- /dev/null +++ b/examples/Optimization/airfoils/NACA_0018_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.277853 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 7.40293088030186e-03 + 9.89671379974747e-01 5.52312701646428e-03 + 9.64477131182153e-01 2.48535959199292e-03 + 9.39158624174899e-01 1.50473515887706e-03 + 9.13813162279310e-01 2.76632310473288e-03 + 8.88553591831403e-01 2.67289317456605e-03 + 8.63480304357990e-01 1.25212903431862e-03 + 8.38670008821752e-01 -1.30558063733301e-03 + 8.14184038980280e-01 -4.88132537219822e-03 + 7.90073507481042e-01 -9.41733442728799e-03 + 7.66396243180071e-01 -1.48824286806251e-02 + 7.43171762127060e-01 -2.11375614462018e-02 + 7.20393063763985e-01 -2.79720058036821e-02 + 6.98115514389012e-01 -3.52505652104797e-02 + 6.76338951051125e-01 -4.28545172802418e-02 + 6.54963698148296e-01 -5.06468535065558e-02 + 6.33966484340103e-01 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b/examples/Optimization/airfoils/NACA_0021.csv new file mode 100644 index 00000000..7079c688 --- /dev/null +++ b/examples/Optimization/airfoils/NACA_0021.csv @@ -0,0 +1,37 @@ +100.0001,0 +100,0.221 +95,1.412 +90,2.534 +80,4.591 +70,6.412 +60,7.986 +50,9.265 +40,10.156 +30,10.504 +25,10.397 +20,10.04 +15,9.354 +10,8.195 +7.5,7.35 +5,6.221 +2.5,4.576 +1.25,3.315 +0,0 +1.25,-3.315 +2.5,-4.576 +5,-6.221 +7.5,-7.35 +10,-8.195 +15,-9.354 +20,-10.04 +25,-10.397 +30,-10.504 +40,-10.156 +50,-9.265 +60,-7.986 +70,-6.412 +80,-4.591 +90,-2.534 +95,-1.412 +100,-0.221 +100.0001,0 \ No newline at end of file diff --git a/examples/Optimization/airfoils/NACA_0021.dat b/examples/Optimization/airfoils/NACA_0021.dat new file mode 100644 index 00000000..086fb2f0 --- /dev/null +++ b/examples/Optimization/airfoils/NACA_0021.dat @@ -0,0 +1,1211 @@ +Title: NACA0021 +Thickness to Chord Ratio: 0.21 +Zero Lift AOA (deg): 0.0 +Reverse Camber Direction: 0 + +Reynolds Number: 1e4 +BV Dyn. 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Stall Model - Positive Stall AOA (deg): 1.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -1.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 5.73 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1 +LB Dyn. 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Stall Model - Positive Stall AOA (deg): 3.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -3.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 4.309 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 0.526 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -0.526 +AOA (deg) CL CD Cm25 +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -0.480200000000000 0.405000000000000 0 +-22 -0.334500000000000 0.329000000000000 0 +-20 -0.241400000000000 0.282000000000000 0 +-18 -0.161900000000000 0.238000000000000 0 +-16 -0.0981000000000000 0.196000000000000 0 +-14 -0.0833000000000000 0.158000000000000 0 +-12 -0.166000000000000 0.123000000000000 0 +-10 -0.269100000000000 0.0620000000000000 0 +-9 -0.316200000000000 0.0343000000000000 0 +-8 -0.342000000000000 0.0319000000000000 0 +-7 -0.342700000000000 0.0297000000000000 0 +-6 -0.338200000000000 0.0279000000000000 0 +-5 -0.308600000000000 0.0264000000000000 0 +-4 -0.273000000000000 0.0253000000000000 0 +-3 -0.210300000000000 0.0243000000000000 0 +-2 -0.146500000000000 0.0237000000000000 0 +-1 -0.0752000000000000 0.0233000000000000 0 +0 0 0.0232000000000000 0 +1 0.0752000000000000 0.0233000000000000 0 +2 0.146500000000000 0.0237000000000000 0 +3 0.210300000000000 0.0243000000000000 0 +4 0.273000000000000 0.0253000000000000 0 +5 0.308600000000000 0.0264000000000000 0 +6 0.338200000000000 0.0279000000000000 0 +7 0.342700000000000 0.0297000000000000 0 +8 0.342000000000000 0.0319000000000000 0 +9 0.316200000000000 0.0343000000000000 0 +10 0.269100000000000 0.0620000000000000 0 +12 0.166000000000000 0.123000000000000 0 +14 0.0833000000000000 0.158000000000000 0 +16 0.0981000000000000 0.196000000000000 0 +18 0.161900000000000 0.238000000000000 0 +20 0.241400000000000 0.282000000000000 0 +22 0.334500000000000 0.329000000000000 0 +25 0.480200000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 + +Reynolds Number: 8e4 +BV Dyn. Stall Model - Positive Stall AOA (deg): 4.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -4.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 5.277 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 0.829 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -0.829 +AOA (deg) CL CD Cm25 +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -0.529700000000000 0.405000000000000 0 +-22 -0.409100000000000 0.329000000000000 0 +-20 -0.347500000000000 0.282000000000000 0 +-18 -0.322100000000000 0.238000000000000 0 +-16 -0.349900000000000 0.196000000000000 0 +-14 -0.429600000000000 0.158000000000000 0 +-12 -0.522800000000000 0.123000000000000 0 +-11 -0.556400000000000 0.0700000000000000 0 +-10 -0.578000000000000 0.0297000000000000 0 +-9 -0.587400000000000 0.0273000000000000 0 +-8 -0.575100000000000 0.0252000000000000 0 +-7 -0.544500000000000 0.0233000000000000 0 +-6 -0.495300000000000 0.0217000000000000 0 +-5 -0.432400000000000 0.0204000000000000 0 +-4 -0.356400000000000 0.0194000000000000 0 +-3 -0.273100000000000 0.0186000000000000 0 +-2 -0.183900000000000 0.0181000000000000 0 +-1 -0.0921000000000000 0.0178000000000000 0 +0 0 0.0177000000000000 0 +1 0.0921000000000000 0.0178000000000000 0 +2 0.183900000000000 0.0181000000000000 0 +3 0.273100000000000 0.0186000000000000 0 +4 0.356400000000000 0.0194000000000000 0 +5 0.432400000000000 0.0204000000000000 0 +6 0.495300000000000 0.0217000000000000 0 +7 0.544500000000000 0.0233000000000000 0 +8 0.575100000000000 0.0252000000000000 0 +9 0.587400000000000 0.0273000000000000 0 +10 0.578000000000000 0.0297000000000000 0 +11 0.556400000000000 0.0700000000000000 0 +12 0.522800000000000 0.123000000000000 0 +14 0.429600000000000 0.158000000000000 0 +16 0.349900000000000 0.196000000000000 0 +18 0.322100000000000 0.238000000000000 0 +20 0.347500000000000 0.282000000000000 0 +22 0.409100000000000 0.329000000000000 0 +25 0.529700000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 + +Reynolds Number: 1.6e5 +BV Dyn. Stall Model - Positive Stall AOA (deg): 5.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -5.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 5.371 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.031 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.031 +AOA (deg) CL CD Cm25 +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -0.666400000000000 0.405000000000000 0 +-22 -0.602300000000000 0.329000000000000 0 +-20 -0.592000000000000 0.282000000000000 0 +-18 -0.609800000000000 0.238000000000000 0 +-16 -0.648700000000000 0.196000000000000 0 +-14 -0.699300000000000 0.158000000000000 0 +-13 -0.725500000000000 0.0860000000000000 0 +-12 -0.736300000000000 0.0292000000000000 0 +-11 -0.744300000000000 0.0266000000000000 0 +-10 -0.737400000000000 0.0243000000000000 0 +-9 -0.714800000000000 0.0222000000000000 0 +-8 -0.674500000000000 0.0204000000000000 0 +-7 -0.620900000000000 0.0187000000000000 0 +-6 -0.548600000000000 0.0174000000000000 0 +-5 -0.468700000000000 0.0163000000000000 0 +-4 -0.380000000000000 0.0155000000000000 0 +-3 -0.286100000000000 0.0148000000000000 0 +-2 -0.187900000000000 0.0143000000000000 0 +-1 -0.0842000000000000 0.0140000000000000 0 +0 0 0.0139000000000000 0 +1 0.0842000000000000 0.0140000000000000 0 +2 0.187900000000000 0.0143000000000000 0 +3 0.286100000000000 0.0148000000000000 0 +4 0.380000000000000 0.0155000000000000 0 +5 0.468700000000000 0.0163000000000000 0 +6 0.548600000000000 0.0174000000000000 0 +7 0.620900000000000 0.0187000000000000 0 +8 0.674500000000000 0.0204000000000000 0 +9 0.714800000000000 0.0222000000000000 0 +10 0.737400000000000 0.0243000000000000 0 +11 0.744300000000000 0.0266000000000000 0 +12 0.736300000000000 0.0292000000000000 0 +13 0.725500000000000 0.0860000000000000 0 +14 0.699300000000000 0.158000000000000 0 +16 0.648700000000000 0.196000000000000 0 +18 0.609800000000000 0.238000000000000 0 +20 0.592000000000000 0.282000000000000 0 +22 0.602300000000000 0.329000000000000 0 +25 0.666400000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 + +Reynolds Number: 3.6e5 +BV Dyn. Stall Model - Positive Stall AOA (deg): 5.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -5.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.32 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.32 +AOA (deg) CL CD Cm25 +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -0.886600000000000 0.405000000000000 0 +-22 -0.845300000000000 0.329000000000000 0 +-20 -0.839700000000000 0.282000000000000 0 +-18 -0.848900000000000 0.238000000000000 0 +-16 -0.871700000000000 0.196000000000000 0 +-15 -0.884000000000000 0.104000000000000 0 +-14 -0.893700000000000 0.0286000000000000 0 +-13 -0.897300000000000 0.0260000000000000 0 +-12 -0.893800000000000 0.0237000000000000 0 +-11 -0.877900000000000 0.0215000000000000 0 +-10 -0.850000000000000 0.0195000000000000 0 +-9 -0.802600000000000 0.0178000000000000 0 +-8 -0.743400000000000 0.0163000000000000 0 +-7 -0.672800000000000 0.0149000000000000 0 +-6 -0.589100000000000 0.0138000000000000 0 +-5 -0.499800000000000 0.0129000000000000 0 +-4 -0.404400000000000 0.0122000000000000 0 +-3 -0.302400000000000 0.0117000000000000 0 +-2 -0.220000000000000 0.0113000000000000 0 +-1 -0.110000000000000 0.0111000000000000 0 +0 0 0.0111000000000000 0 +1 0.110000000000000 0.0111000000000000 0 +2 0.220000000000000 0.0113000000000000 0 +3 0.302400000000000 0.0117000000000000 0 +4 0.404400000000000 0.0122000000000000 0 +5 0.499800000000000 0.0129000000000000 0 +6 0.589100000000000 0.0138000000000000 0 +7 0.672800000000000 0.0149000000000000 0 +8 0.743400000000000 0.0163000000000000 0 +9 0.802600000000000 0.0178000000000000 0 +10 0.850000000000000 0.0195000000000000 0 +11 0.877900000000000 0.0215000000000000 0 +12 0.893800000000000 0.0237000000000000 0 +13 0.897300000000000 0.0260000000000000 0 +14 0.893700000000000 0.0286000000000000 0 +15 0.884000000000000 0.104000000000000 0 +16 0.871700000000000 0.196000000000000 0 +18 0.848900000000000 0.238000000000000 0 +20 0.839700000000000 0.282000000000000 0 +22 0.845300000000000 0.329000000000000 0 +25 0.886600000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 + +Reynolds Number: 7e5 +BV Dyn. Stall Model - Positive Stall AOA (deg): 6.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -6.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.54 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.54 +AOA (deg) CL CD Cm25 +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -1.03500000000000 0.405000000000000 0 +-22 -0.994000000000000 0.329000000000000 0 +-20 -0.985800000000000 0.282000000000000 0 +-18 -0.991100000000000 0.238000000000000 0 +-17 -0.997300000000000 0.125000000000000 0 +-16 -1.00560000000000 0.0295000000000000 0 +-15 -1.01060000000000 0.0269000000000000 0 +-14 -1.01220000000000 0.0244000000000000 0 +-13 -1.00200000000000 0.0223000000000000 0 +-12 -0.984300000000000 0.0202000000000000 0 +-11 -0.954300000000000 0.0184000000000000 0 +-10 -0.909100000000000 0.0166000000000000 0 +-9 -0.849800000000000 0.0152000000000000 0 +-8 -0.780200000000000 0.0138000000000000 0 +-7 -0.698800000000000 0.0126000000000000 0 +-6 -0.610000000000000 0.0117000000000000 0 +-5 -0.514600000000000 0.0109000000000000 0 +-4 -0.412800000000000 0.0103000000000000 0 +-3 -0.330000000000000 0.00980000000000000 0 +-2 -0.220000000000000 0.00960000000000000 0 +-1 -0.110000000000000 0.00940000000000000 0 +0 0 0.00940000000000000 0 +1 0.110000000000000 0.00940000000000000 0 +2 0.220000000000000 0.00960000000000000 0 +3 0.330000000000000 0.00980000000000000 0 +4 0.412800000000000 0.0103000000000000 0 +5 0.514600000000000 0.0109000000000000 0 +6 0.610000000000000 0.0117000000000000 0 +7 0.698800000000000 0.0126000000000000 0 +8 0.780200000000000 0.0138000000000000 0 +9 0.849800000000000 0.0152000000000000 0 +10 0.909100000000000 0.0166000000000000 0 +11 0.954300000000000 0.0184000000000000 0 +12 0.984300000000000 0.0202000000000000 0 +13 1.00200000000000 0.0223000000000000 0 +14 1.01220000000000 0.0244000000000000 0 +15 1.01060000000000 0.0269000000000000 0 +16 1.00560000000000 0.0295000000000000 0 +17 0.997300000000000 0.125000000000000 0 +18 0.991100000000000 0.238000000000000 0 +20 0.985800000000000 0.282000000000000 0 +22 0.994000000000000 0.329000000000000 0 +25 1.03500000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 + +Reynolds Number: 1e6 +BV Dyn. Stall Model - Positive Stall AOA (deg): 6.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -6.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.65 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.65 +AOA (deg) CL CD Cm25 +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -1.10180000000000 0.405000000000000 0 +-22 -1.06440000000000 0.329000000000000 0 +-20 -1.05540000000000 0.282000000000000 0 +-18 -1.05880000000000 0.135000000000000 0 +-17 -1.06410000000000 0.0300000000000000 0 +-16 -1.06900000000000 0.0273000000000000 0 +-15 -1.07090000000000 0.0248000000000000 0 +-14 -1.06570000000000 0.0226000000000000 0 +-13 -1.04920000000000 0.0206000000000000 0 +-12 -1.02570000000000 0.0187000000000000 0 +-11 -0.986200000000000 0.0170000000000000 0 +-10 -0.936400000000000 0.0154000000000000 0 +-9 -0.869400000000000 0.0140000000000000 0 +-8 -0.793900000000000 0.0128000000000000 0 +-7 -0.710200000000000 0.0117000000000000 0 +-6 -0.619100000000000 0.0108000000000000 0 +-5 -0.519200000000000 0.0101000000000000 0 +-4 -0.440000000000000 0.00960000000000000 0 +-3 -0.330000000000000 0.00920000000000000 0 +-2 -0.220000000000000 0.00900000000000000 0 +-1 -0.110000000000000 0.00890000000000000 0 +0 0 0.00890000000000000 0 +1 0.110000000000000 0.00890000000000000 0 +2 0.220000000000000 0.00900000000000000 0 +3 0.330000000000000 0.00920000000000000 0 +4 0.440000000000000 0.00960000000000000 0 +5 0.519200000000000 0.0101000000000000 0 +6 0.619100000000000 0.0108000000000000 0 +7 0.710200000000000 0.0117000000000000 0 +8 0.793900000000000 0.0128000000000000 0 +9 0.869400000000000 0.0140000000000000 0 +10 0.936400000000000 0.0154000000000000 0 +11 0.986200000000000 0.0170000000000000 0 +12 1.02570000000000 0.0187000000000000 0 +13 1.04920000000000 0.0206000000000000 0 +14 1.06570000000000 0.0226000000000000 0 +15 1.07090000000000 0.0248000000000000 0 +16 1.06900000000000 0.0273000000000000 0 +17 1.06410000000000 0.0300000000000000 0 +18 1.05880000000000 0.135000000000000 0 +20 1.05540000000000 0.282000000000000 0 +22 1.06440000000000 0.329000000000000 0 +25 1.10180000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 + +Reynolds Number: 2e6 +BV Dyn. Stall Model - Positive Stall AOA (deg): 6.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -6.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.65 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.65 +AOA (deg) CL CD Cm25 +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -1.22300000000000 0.405000000000000 0 +-22 -1.18930000000000 0.329000000000000 0 +-20 -1.18120000000000 0.282000000000000 0 +-19 -1.17970000000000 0.145000000000000 0 +-18 -1.18140000000000 0.0285000000000000 0 +-17 -1.18240000000000 0.0260000000000000 0 +-16 -1.18230000000000 0.0236000000000000 0 +-15 -1.17470000000000 0.0215000000000000 0 +-14 -1.15800000000000 0.0196000000000000 0 +-13 -1.13050000000000 0.0179000000000000 0 +-12 -1.09060000000000 0.0162000000000000 0 +-11 -1.03980000000000 0.0148000000000000 0 +-10 -0.973900000000000 0.0135000000000000 0 +-9 -0.898600000000000 0.0124000000000000 0 +-8 -0.814300000000000 0.0114000000000000 0 +-7 -0.725400000000000 0.0105000000000000 0 +-6 -0.626800000000000 0.00980000000000000 0 +-5 -0.550000000000000 0.00920000000000000 0 +-4 -0.440000000000000 0.00890000000000000 0 +-3 -0.330000000000000 0.00860000000000000 0 +-2 -0.220000000000000 0.00840000000000000 0 +-1 -0.110000000000000 0.00830000000000000 0 +0 0 0.00820000000000000 0 +1 0.110000000000000 0.00830000000000000 0 +2 0.220000000000000 0.00840000000000000 0 +3 0.330000000000000 0.00860000000000000 0 +4 0.440000000000000 0.00890000000000000 0 +5 0.550000000000000 0.00920000000000000 0 +6 0.626800000000000 0.00980000000000000 0 +7 0.725400000000000 0.0105000000000000 0 +8 0.814300000000000 0.0114000000000000 0 +9 0.898600000000000 0.0124000000000000 0 +10 0.973900000000000 0.0135000000000000 0 +11 1.03980000000000 0.0148000000000000 0 +12 1.09060000000000 0.0162000000000000 0 +13 1.13050000000000 0.0179000000000000 0 +14 1.15800000000000 0.0196000000000000 0 +15 1.17470000000000 0.0215000000000000 0 +16 1.18230000000000 0.0236000000000000 0 +17 1.18240000000000 0.0260000000000000 0 +18 1.18140000000000 0.0285000000000000 0 +19 1.17970000000000 0.145000000000000 0 +20 1.18120000000000 0.282000000000000 0 +22 1.18930000000000 0.329000000000000 0 +25 1.22300000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 + +Reynolds Number: 5e6 +BV Dyn. Stall Model - Positive Stall AOA (deg): 6.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -6.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.76 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.76 +AOA (deg) CL CD Cm25 +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -1.34760000000000 0.405000000000000 0 +-22 -1.31300000000000 0.329000000000000 0 +-20 -1.30540000000000 0.0293000000000000 0 +-19 -1.30660000000000 0.0268000000000000 0 +-18 -1.30310000000000 0.0245000000000000 0 +-17 -1.29770000000000 0.0224000000000000 0 +-16 -1.28600000000000 0.0205000000000000 0 +-15 -1.26800000000000 0.0186000000000000 0 +-14 -1.24100000000000 0.0170000000000000 0 +-13 -1.19790000000000 0.0156000000000000 0 +-12 -1.14530000000000 0.0143000000000000 0 +-11 -1.07870000000000 0.0132000000000000 0 +-10 -1.00490000000000 0.0121000000000000 0 +-9 -0.922200000000000 0.0112000000000000 0 +-8 -0.833400000000000 0.0104000000000000 0 +-7 -0.735400000000000 0.00970000000000000 0 +-6 -0.660000000000000 0.00910000000000000 0 +-5 -0.550000000000000 0.00860000000000000 0 +-4 -0.440000000000000 0.00830000000000000 0 +-3 -0.330000000000000 0.00810000000000000 0 +-2 -0.220000000000000 0.00790000000000000 0 +-1 -0.110000000000000 0.00780000000000000 0 +0 0 0.00780000000000000 0 +1 0.110000000000000 0.00780000000000000 0 +2 0.220000000000000 0.00790000000000000 0 +3 0.330000000000000 0.00810000000000000 0 +4 0.440000000000000 0.00830000000000000 0 +5 0.550000000000000 0.00860000000000000 0 +6 0.660000000000000 0.00910000000000000 0 +7 0.735400000000000 0.00970000000000000 0 +8 0.833400000000000 0.0104000000000000 0 +9 0.922200000000000 0.0112000000000000 0 +10 1.00490000000000 0.0121000000000000 0 +11 1.07870000000000 0.0132000000000000 0 +12 1.14530000000000 0.0143000000000000 0 +13 1.19790000000000 0.0156000000000000 0 +14 1.24100000000000 0.0170000000000000 0 +15 1.26800000000000 0.0186000000000000 0 +16 1.28600000000000 0.0205000000000000 0 +17 1.29770000000000 0.0224000000000000 0 +18 1.30310000000000 0.0245000000000000 0 +19 1.30660000000000 0.0268000000000000 0 +20 1.30540000000000 0.0293000000000000 0 +22 1.31300000000000 0.329000000000000 0 +25 1.34760000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 + +Reynolds Number: 8e6 +BV Dyn. Stall Model - Positive Stall AOA (deg): 10.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -10.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.131 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.82 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.82 +AOA (deg) CL CD Cm25 +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-22 -1.45100000000000 0.329000000000000 0 +-20 -1.43500000000000 0.282000000000000 0 +-18 -1.41500000000000 0.135000000000000 0 +-16 -1.37700000000000 0.0199000000000000 0 +-15 -1.34400000000000 0.0184000000000000 0 +-14 -1.30100000000000 0.0170000000000000 0 +-13 -1.24800000000000 0.0157000000000000 0 +-12 -1.18200000000000 0.0145000000000000 0 +-11 -1.10800000000000 0.0134000000000000 0 +-10 -1.02400000000000 0.0124000000000000 0 +-9 -0.935000000000000 0.0115000000000000 0 +-8 -0.841000000000000 0.0107000000000000 0 +-7 -0.744000000000000 0.00990000000000000 0 +-6 -0.639000000000000 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Stall Model - Positive Stall AOA (deg): 5.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -5.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.21 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.21 +AOA (deg) CL CD Cm25 +-180.090000000000 -0.00580000000000000 0.0171000000000000 0 +-175.090000000000 0.186200000000000 0.0308000000000000 0 +-170.010000000000 0.659500000000000 0.0871000000000000 0 +-165.020000000000 0.483400000000000 0.195500000000000 0 +-160 0.479600000000000 0.272600000000000 0 +-154.980000000000 0.552700000000000 0.384000000000000 0 +-149.910000000000 0.709900000000000 0.571500000000000 0 +-144.890000000000 0.860600000000000 0.804300000000000 0 +-139.950000000000 0.916100000000000 0.994800000000000 0 +-134.940000000000 0.890000000000000 1.14290000000000 0 +-129.930000000000 0.897600000000000 1.35270000000000 0 +-124.920000000000 0.823200000000000 1.49910000000000 0 +-119.910000000000 0.742900000000000 1.64450000000000 0 +-114.990000000000 0.633000000000000 1.75570000000000 0 +-109.990000000000 0.507700000000000 1.84560000000000 0 +-105.020000000000 0.370600000000000 1.96190000000000 0 +-100.050000000000 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Stall Model - Positive Stall AOA (deg): 4.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -4.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.73 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.4 +LB Dyn. 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Stall Model - Positive Stall AOA (deg): 4.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -4.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.451 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.35 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.35 +AOA (deg) CL CD Cm25 +-180.080000000000 -0.00830000000000000 0.0151000000000000 0 +-175.090000000000 0.0100000000000000 0.0226000000000000 0 +-169.950000000000 0.574700000000000 0.0774000000000000 0 +-165.040000000000 0.496300000000000 0.217800000000000 0 +-159.990000000000 0.465600000000000 0.283500000000000 0 +-154.960000000000 0.577700000000000 0.411400000000000 0 +-149.900000000000 0.743800000000000 0.609300000000000 0 +-144.880000000000 0.838700000000000 0.795600000000000 0 +-139.940000000000 0.901500000000000 0.987600000000000 0 +-134.930000000000 0.886400000000000 1.14160000000000 0 +-129.950000000000 0.857000000000000 1.29850000000000 0 +-124.910000000000 0.802900000000000 1.46040000000000 0 +-119.950000000000 0.805500000000000 1.65790000000000 0 +-115.020000000000 0.687600000000000 1.77070000000000 0 +-110.020000000000 0.548300000000000 1.85290000000000 0 +-105.040000000000 0.403300000000000 1.92880000000000 0 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Stall Model - Positive Stall AOA (deg): 6.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -6.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.32 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.32 +AOA (deg) CL CD Cm25 +-180.080000000000 -0.00830000000000000 0.0151000000000000 0 +-175.090000000000 0.0100000000000000 0.0226000000000000 0 +-169.950000000000 0.574700000000000 0.0774000000000000 0 +-165.040000000000 0.496300000000000 0.217800000000000 0 +-159.990000000000 0.465600000000000 0.283500000000000 0 +-154.960000000000 0.577700000000000 0.411400000000000 0 +-149.900000000000 0.743800000000000 0.609300000000000 0 +-144.880000000000 0.838700000000000 0.795600000000000 0 +-139.940000000000 0.901500000000000 0.987600000000000 0 +-134.930000000000 0.886400000000000 1.14160000000000 0 +-129.950000000000 0.857000000000000 1.29850000000000 0 +-124.910000000000 0.802900000000000 1.46040000000000 0 +-119.950000000000 0.805500000000000 1.65790000000000 0 +-115.020000000000 0.687600000000000 1.77070000000000 0 +-110.020000000000 0.548300000000000 1.85290000000000 0 +-105.040000000000 0.403300000000000 1.92880000000000 0 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Stall Model - Positive Stall AOA (deg): 5.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -5.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.32 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.32 +AOA (deg) CL CD Cm25 +-180.080000000000 -0.00830000000000000 0.0151000000000000 0 +-175.090000000000 0.0100000000000000 0.0226000000000000 0 +-169.950000000000 0.574700000000000 0.0774000000000000 0 +-165.040000000000 0.496300000000000 0.217800000000000 0 +-159.990000000000 0.465600000000000 0.283500000000000 0 +-154.960000000000 0.577700000000000 0.411400000000000 0 +-149.900000000000 0.743800000000000 0.609300000000000 0 +-144.880000000000 0.838700000000000 0.795600000000000 0 +-139.940000000000 0.901500000000000 0.987600000000000 0 +-134.930000000000 0.886400000000000 1.14160000000000 0 +-129.950000000000 0.857000000000000 1.29850000000000 0 +-124.910000000000 0.802900000000000 1.46040000000000 0 +-119.950000000000 0.805500000000000 1.65790000000000 0 +-115.020000000000 0.687600000000000 1.77070000000000 0 +-110.020000000000 0.548300000000000 1.85290000000000 0 +-105.040000000000 0.403300000000000 1.92880000000000 0 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+0.008856375,0.093690657 +0.015708419,0.124344944 +0.024471742,0.154508497 +0.035111757,0.184062276 +0.047586474,0.212889646 +0.06184666,0.240876837 +0.077836037,0.267913397 +0.095491503,0.293892626 +0.114743379,0.318711995 +0.135515686,0.342273553 +0.157726447,0.364484314 +0.181288005,0.385256621 +0.206107374,0.404508497 +0.232086603,0.422163963 +0.259123163,0.43815334 +0.287110354,0.452413526 +0.315937724,0.464888243 +0.345491503,0.475528258 +0.375655056,0.484291581 +0.406309343,0.491143625 +0.437333383,0.496057351 +0.46860474,0.499013364 +0.5,0.5 +0.53139526,0.499013364 +0.562666617,0.496057351 +0.593690657,0.491143625 +0.624344944,0.484291581 +0.654508497,0.475528258 +0.684062276,0.464888243 +0.712889646,0.452413526 +0.740876837,0.43815334 +0.767913397,0.422163963 +0.793892626,0.404508497 +0.818711995,0.385256621 +0.842273553,0.364484314 +0.864484314,0.342273553 +0.885256621,0.318711995 +0.904508497,0.293892626 +0.922163963,0.267913397 +0.93815334,0.240876837 +0.952413526,0.212889646 +0.964888243,0.184062276 +0.975528258,0.154508497 +0.984291581,0.124344944 +0.991143625,0.093690657 +0.996057351,0.062666617 +0.999013364,0.03139526 diff --git a/examples/Optimization/airfoils/e212-il.csv b/examples/Optimization/airfoils/e212-il.csv new file mode 100644 index 00000000..f64b838b --- /dev/null +++ b/examples/Optimization/airfoils/e212-il.csv @@ -0,0 +1,62 @@ +100.000000,0.000000 +99.676000,0.092000 +98.759000,0.372000 +97.346000,0.803000 +95.472000,1.307000 +93.124000,1.844000 +90.316000,2.418000 +87.085000,3.023000 +83.474000,3.645000 +79.525000,4.269000 +75.283000,4.881000 +70.796000,5.465000 +66.112000,6.008000 +61.282000,6.496000 +56.355000,6.915000 +51.383000,7.256000 +46.416000,7.507000 +41.502000,7.660000 +36.689000,7.708000 +32.023000,7.647000 +27.548000,7.473000 +23.303000,7.188000 +19.326000,6.794000 +15.651000,6.295000 +12.309000,5.701000 +9.327000,5.023000 +6.729000,4.275000 +4.534000,3.473000 +2.758000,2.636000 +1.410000,1.790000 +0.499000,0.967000 +0.032000,0.224000 +0.0,0.0 +0.122000,-0.398000 +0.800000,-0.970000 +1.984000,-1.532000 +3.648000,-2.045000 +5.780000,-2.486000 +8.363000,-2.840000 +11.379000,-3.097000 +14.808000,-3.252000 +18.621000,-3.301000 +22.790000,-3.248000 +27.280000,-3.099000 +32.051000,-2.861000 +37.059000,-2.548000 +42.257000,-2.175000 +47.590000,-1.759000 +53.003000,-1.320000 +58.434000,-0.878000 +63.819000,-0.452000 +69.090000,-0.063000 +74.179000,0.271000 +79.016000,0.535000 +83.528000,0.713000 +87.643000,0.794000 +91.284000,0.776000 +94.382000,0.659000 +96.851000,0.458000 +98.615000,0.231000 +99.657000,0.061000 +100.000000,0.000000 diff --git a/examples/Optimization/data/NuMAD_Geom_SNL_5MW_D_Carbon_LCDT_ThickFoils_ThinSkin.csv b/examples/Optimization/data/NuMAD_Geom_SNL_5MW_D_Carbon_LCDT_ThickFoils_ThinSkin.csv new file mode 100644 index 00000000..6ad6c14d --- /dev/null +++ b/examples/Optimization/data/NuMAD_Geom_SNL_5MW_D_Carbon_LCDT_ThickFoils_ThinSkin.csv @@ -0,0 +1,24 @@ +SNL_5MW_D_Carbon_LCDT,,,,# Shear webs ->,1,# of stacks ->,7,Stack ID ->,1,2,3,4,5,6,7,Segment ID ->,1,2,3,4,5,6,7,8,9,10,11,12,DP Types,1,2,3,4,5,6,7,8,9,10,11,12,1,2,3,4,5,6,7,8,9,10,11,12,, +,,,,,,# of segments ->,12,Material ID ->,1,2,4,1,1,2,4,,,,,,,,,,,,,,,,,,,,,,,,,,,first entry in the CSV list is the exterior blade surface stack,,,,,,,,,,,,SW1, +Sta.#,Blade span (m),Airfoil Shape File,TE Type,Twist (deg),Chord,xoffset,aero center,Section Label,LE,Panel_Face,Panel_Core,Spar,TE,SW_Face,SW_Core,-blank-,HP_TE,HP_Aft_Panel,HP_Aft_Spar,HP_Fore_Spar,HP_Fore_Panel,HP_LE,LP_LE,LP_Fore_Panel,LP_Aft_Spar,LP_Fore_Spar,LP_Aft_Panel,LP_TE,,,,,,,,,,,,,,HP_TE,HP_Aft_Panel,HP_Aft_Spar,HP_Fore_Spar,HP_Fore_Panel,HP_LE,LP_LE,LP_Fore_Panel,LP_Aft_Spar,LP_Fore_Spar,LP_Aft_Panel,LP_TE,stacks,dps +1,0,NACA_0021,sharp,0,6,0.3,0.2,,12,1,8,12,12,1,8,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +2,6.607,NACA_0021,sharp,0,6,0.3,0.2,,12,1,9,13,12,1,9,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +3,13.215,NACA_0021,sharp,0,6,0.3,0.2,,12,1,9,13,12,1,9,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +4,19.822,NACA_0021,sharp,0,5.498,0.3,0.2,,11,1,8,12,11,1,8,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +5,26.43,NACA_0021,sharp,0,4.431,0.3,0.2,,9,1,7,10,9,1,7,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +6,33.037,NACA_0021,sharp,0,3.806,0.3,0.2,,8,1,6,8,8,1,6,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +7,39.645,NACA_0021,sharp,0,3.435,0.3,0.2,,7,1,5,8,7,1,5,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +8,46.252,NACA_0021,sharp,0,3.205,0.3,0.2,,6,1,5,7,6,1,5,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +9,52.859,NACA_0021,sharp,0,3.068,0.3,0.2,,6,1,5,7,6,1,5,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +10,59.467,NACA_0021,sharp,0,3.003,0.3,0.2,,6,1,4,7,6,1,4,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +11,66.074,NACA_0021,sharp,0,3,0.3,0.2,,6,1,4,7,6,1,4,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +12,72.682,NACA_0021,sharp,0,3.056,0.3,0.2,,6,1,4,7,6,1,4,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +13,79.289,NACA_0021,sharp,0,3.176,0.3,0.2,,6,1,5,7,6,1,5,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +14,85.896,NACA_0021,sharp,0,3.377,0.3,0.2,,7,1,5,8,7,1,5,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +15,92.504,NACA_0021,sharp,0,3.688,0.3,0.2,,7,1,5,8,7,1,5,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +16,99.111,NACA_0021,sharp,0,4.18,0.3,0.2,,8,1,6,9,8,1,6,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +17,105.719,NACA_0021,sharp,0,4.924,0.3,0.2,,10,1,7,11,10,1,7,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +18,112.326,NACA_0021,sharp,0,6,0.3,0.2,,12,1,9,13,12,1,9,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +19,118.934,NACA_0021,sharp,0,6,0.3,0.2,,12,1,9,13,12,1,9,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +20,125.541,NACA_0021,sharp,0,6,0.3,0.2,,12,1,9,13,12,1,9,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +21,132.148,NACA_0021,sharp,0,6,0.3,0.2,,12,1,9,13,12,1,9,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" diff --git a/examples/Optimization/data/NuMAD_Geom_SNL_5MW_D_TaperedTower.csv b/examples/Optimization/data/NuMAD_Geom_SNL_5MW_D_TaperedTower.csv new file mode 100644 index 00000000..3f7a1aa2 --- /dev/null +++ b/examples/Optimization/data/NuMAD_Geom_SNL_5MW_D_TaperedTower.csv @@ -0,0 +1,54 @@ +SNL_5MW_D_Tapered_Tower,,,,# Shear webs ->,0,# of stacks ->,2,Stack ID ->,1,2,Segment ID ->,1,10,DP Types,1,2,1,2,,,,,,,,,,,,,,,,,,,, +,,,,,,# of segments ->,2,Material ID ->,1,2,,,,,,,first entry in the CSV list is the exterior blade surface stack,,,,,,,,,,,,,,,,,,,,, +Sta.#,Blade span (m),Airfoil Shape File,TE Type,Twist (deg),Chord,xoffset,aero center,Section Label,Uni,Skin,-blank-,HP,LP,,,,HP,LP,,,,,,,,,,,,,,,,,,,, +1,0,circular,round,0,5.888066637,0.5,0.25,,89.213,8.921,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, +2,6.607421057,circular,round,0,5.788249614,0.5,0.25,,87.701,8.770,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, +3,13.21484211,circular,round,0,5.684865834,0.5,0.25,,86.134,8.613,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, +4,19.82226317,circular,round,0,5.577578504,0.5,0.25,,84.509,8.451,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, +5,26.42968423,circular,round,0,5.465996871,0.5,0.25,,82.818,8.282,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, +6,33.03710529,circular,round,0,5.349663569,0.5,0.25,,81.056,8.106,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, +7,39.64452634,circular,round,0,5.22803793,0.5,0.25,,79.213,7.921,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, +8,46.2519474,circular,round,0,5.100473576,0.5,0.25,,77.280,7.728,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, +9,52.85936846,circular,round,0,4.966187737,0.5,0.25,,75.245,7.525,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, +10,59.46678951,circular,round,0,4.824218239,0.5,0.25,,73.094,7.309,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, +11,66.07421057,circular,round,0,4.673361587,0.5,0.25,,70.809,7.081,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, +12,72.68163163,circular,round,0,4.512081003,0.5,0.25,,68.365,6.836,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, +13,79.28905268,circular,round,0,4.338364592,0.5,0.25,,65.733,6.573,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, +14,85.89647374,circular,round,0,4.149496455,0.5,0.25,,62.871,6.287,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, +15,92.5038948,circular,round,0,3.941665819,0.5,0.25,,59.722,5.972,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, +16,99.11131586,circular,round,0,3.70924955,0.5,0.25,,56.201,5.620,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, +17,105.7187369,circular,round,0,3.443362258,0.5,0.25,,52.172,5.217,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, +18,112.326158,circular,round,0,3.128502234,0.5,0.25,,47.402,4.740,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, +19,118.933579,circular,round,0,2.732998436,0.5,0.25,,41.409,4.141,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, +20,125.5410001,circular,round,0,2.169182296,0.5,0.25,,32.866,3.287,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, +21,132.1484211,circular,round,0,2,0.5,0.25,,30.303,3.030,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, +,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, +,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, +,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, +,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, +,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, +,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, +,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, +,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, +,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, +,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, +,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, +,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, +,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, +,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, +,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, +,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, +,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, +,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, +,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, +,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, +,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, +,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, +,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, +,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, +,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, +,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, +,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, +,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, +,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, +,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, \ No newline at end of file diff --git a/examples/Optimization/data/NuMAD_Geom_SNL_5MW_Struts.csv b/examples/Optimization/data/NuMAD_Geom_SNL_5MW_Struts.csv new file mode 100644 index 00000000..bf5eeb96 --- /dev/null +++ b/examples/Optimization/data/NuMAD_Geom_SNL_5MW_Struts.csv @@ -0,0 +1,7 @@ +SNL_5MW_D_Carbon_LCDT,,,,# Shear webs ->,1,# of stacks ->,7,Stack ID ->,1,2,3,4,5,6,7,Segment ID ->,1,2,3,4,5,6,7,8,9,10,11,12,DP Types,1,2,3,4,5,6,7,8,9,10,11,12,1,2,3,4,5,6,7,8,9,10,11,12,, +,,,,,,# of segments ->,12,Material ID ->,1,2,4,1,1,2,4,,,,,,,,,,,,,,,,,,,,,,,,,,,first entry in the CSV list is the exterior blade surface stack,,,,,,,,,,,,SW1, +Sta.#,Blade span (m),Airfoil Shape File,TE Type,Twist (deg),Chord,xoffset,aero center,Section Label,LE,Panel_Face,Panel_Core,Spar,TE,SW_Face,SW_Core,-blank-,HP_TE,HP_Aft_Panel,HP_Aft_Spar,HP_Fore_Spar,HP_Fore_Panel,HP_LE,LP_LE,LP_Fore_Panel,LP_Aft_Spar,LP_Fore_Spar,LP_Aft_Panel,LP_TE,,,,,,,,,,,,,,HP_TE,HP_Aft_Panel,HP_Aft_Spar,HP_Fore_Spar,HP_Fore_Panel,HP_LE,LP_LE,LP_Fore_Panel,LP_Aft_Spar,LP_Fore_Spar,LP_Aft_Panel,LP_TE,stacks,dps +1,0,NACA_0021,sharp,0,6,0.3,0.2,,12,1,8,12,12,1,8,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +2,6.607,NACA_0021,sharp,0,6,0.3,0.2,,12,1,8,12,12,1,8,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +3,13.215,NACA_0021,sharp,0,6,0.3,0.2,,12,1,8,12,12,1,8,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +4,19.822,NACA_0021,sharp,0,6,0.3,0.2,,12,1,8,12,12,1,8,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" diff --git a/examples/Optimization/data/NuMAD_Materials_SNL_5MW.csv b/examples/Optimization/data/NuMAD_Materials_SNL_5MW.csv new file mode 100644 index 00000000..d010fba4 --- /dev/null +++ b/examples/Optimization/data/NuMAD_Materials_SNL_5MW.csv @@ -0,0 +1,10 @@ +,,,,Ex,Ey,Ez,Gxy,Gyz,Gxz,prxy,pryz,prxz,,,,,,,,,,,,,,,,,,,,, +,,Type,Layer Thickness,E11,E22,,G12,,,nu12,,,density,UTSx,UCSx,UTSy,UCSy,UTSz,UCSz,Cost,Reference,SN_stressMpa,SN_stressMpa,SN_stressMpa,SN_stressMpa,SN_stressMpa,SN_stressMpa,Log_SN_cycles2Fail,Log_SN_cycles2Fail,Log_SN_cycles2Fail,Log_SN_cycles2Fail,Log_SN_cycles2Fail,Log_SN_cycles2Fail +Material ID,,,[mm],[MPa],[MPa],[MPa],[MPa],[MPa],[MPa],[-],[-],[-],[kg/m3],[MPa],[MPa],[MPa],[MPa],[MPa],[MPa],[$/kg],,,,,,,,,,,,, +1,Generic_Pultrusion,orthotropic,1,27000,6000,6000,3000,2500,2500,.26,.36,.26,1850,400,200,100,200,100,200,3.0,,400,350,325,275,200,0,0,1,2,4,6,20 +2,Generic_Skin,orthotropic,1,27000,6000,6000,3000,2500,2500,.26,.36,.26,1850,400,200,100,200,100,200,3.0,,400,350,325,275,200,0,0,1,2,4,6,20 +3,steel,orthotropic,1,199948,199948,199948,76877,76877,76877,0.3,0.3,0.3,7861.092935,420,250,420,250,420,250,1.0,,420,415,375,275,190,0.0,0,1,2,4,6,20 +4,Foam,orthotropic,1,1000,1000,1000,100,100,100,0.3,0.3,0.3,100,50,50,50,50,50,50,.1,,50,45,40,35,20,0.0,0,1,2,4,6,20 +,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, +,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, +,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, \ No newline at end of file diff --git a/examples/dev/modeling_options_OWENS_windioExample.yml b/examples/Optimization/modeling_options_OWENS_windioExample.yml similarity index 100% rename from examples/dev/modeling_options_OWENS_windioExample.yml rename to examples/Optimization/modeling_options_OWENS_windioExample.yml diff --git a/examples/Optimization/optimizationExample.jl b/examples/Optimization/optimizationExample.jl new file mode 100644 index 00000000..cef0dc10 --- /dev/null +++ b/examples/Optimization/optimizationExample.jl @@ -0,0 +1,192 @@ +# WindIO Yaml File Contains, for the turbine: +# Assembly: general size and turbulence conditions +# Components: general blade, tower, strut shape and joints +# Airfoils: geometry, polars across Reynolds numbers +# materials: material properties +# Control: gains +# Environment: properties such as density +# BOS: balance of system variables +# Costs: cost components + +# As of the writing of this file, the following components have their own files but are planned to be switched to the WindIO file input +# Airfoils: airfoil polar files (see examples/Optimization/airfoils/ .dat files), airfoil geometry (see examples/Optimization/airfoils/ .txt files) +# Components->internal structure: Numad Files (see the examples/Optimization/data files and page 85 of https://energy.sandia.gov/wp-content/gallery/uploads/NuMAD_UserGuide_SAND2012-7028.pdf). +# Materials: Numad Files in the examples/Optimization/data folder, see also page 85 of https://energy.sandia.gov/wp-content/gallery/uploads/NuMAD_UserGuide_SAND2012-7028.pdf. +# The specifc items being used from the WindIO yaml format currently (which is subject to rapid development) can be seen in OWENS.jl/src/windio.jl + +# Then the OWENS modeling options currently control +# Controls: currently constant RPM (in work is to expose the scripting options of the discon and custom control options at the super simple file level) +# analysisType = "M" for modal, "S" for steady, "TNB" for time newmark time stepping (must be paired with TNB or GX structural models), "ROM" time stepping (must be paired with ROM structural model), +# turbineType: "Darrieus" (where the blade ends connect to the tower), "H-VAWT" (where the blade ends do not connect to the tower), "ARCUS" where there are only blades and a cable for each blade from the top to the stubby tower base. +# eta: blade mount point ratio, or the chordwise normalized position of the rotation axis on the airfoil, extremely important as it changes the effective pitch offset for a VAWT +# towerHeight: Base tower offset to the blades in the mesh +# Vinf: Windspeed if ifw==false, or if WindType=1 +# RPM: Rotational rate if constant RPM control, is also the initialized RPM +# Nslices: int, Number of vertical slices in the strip theory to get the simplified aero model to be 3D +# ntheta: int, Number of azimuthal discretizations of the simplified aero model, if active, must by wholly divisible by NBlades +# structuralModel: TNB time newmark beta time stepping linear or nonlinear, ROM reduced order modal linear or nonlinear, GX geometrically exact beam theory +# ntelem: int, number of tower elements, in the automatically generated mesh +# nbelem: int, number of blade elements, in the automatically generated mesh +# ncelem: int, number of cable elements, if active, in the automatically generated mesh +# nselem: int, number of strut elements, in the automatically generated mesh +# ifw: true or false, tells the AC or DMS models to use constant inflow or to read the specified windINPfilename +# WindType: Inflow wind wind type (1 2 3), this is automatically handled by the DLC processor when it is used +# AModel: Aero model, "AC" actuator cylinder (slower but slightly more accurate with array capability at the planar aero only level) "DMS" (faster and nearly as accurate) or "AD" (aerodyn interface, specifically OLAF, which is a relatively slow but higher fidelity vortex line wake model. This includes strut drag and tip losses.) +# windINPfilename: .bts or .inp files, see inflow wind documentation. If running with the DLC script, it will automatically generate these and run with them, and not generate them if they already exist unless told to do so. +# ifw_libfile: path to the inflow wind interface library, "nothing" if you are using the one that is automatically build (on mac/linux) with OWENSOpenFASTWrappers.jl +# numTS: total number of time steps +# delta_t: time step, in seconds +# NuMad_geom_xlscsv_file_twr: numad file inputs for twr geom/composite inputs, this is also where the airfoil name is specified +# NuMad_mat_xlscsv_file_twr: numad file inputs for twr materials +# NuMad_geom_xlscsv_file_bld: numad file inputs for bld geom/composite inputs, this is also where the airfoil name is specified +# NuMad_mat_xlscsv_file_bld: numad file inputs for bld materials +# NuMad_geom_xlscsv_file_strut: numad file inputs for strut geom/composite inputs, this is also where the airfoil name is specified +# NuMad_mat_xlscsv_file_strut: numad file inputs for strut materials +# adi_lib: path to the aerodyn interface library, "nothing" if you are using the one that is automatically build (on mac/linux) with OWENSOpenFASTWrappers.jl + + +import OWENS # Main module for OWENS +import HDF5 # used for loading and saving binary HDF5 files that OWENS saves +import YAML # used to load YAML files and create dictionaries of the inputs +import OrderedCollections # used by the YAML reader to create a dictionary that is in the same order as the file +import FLOWMath # used to create optimization friendly splines and max calculations +import Statistics:mean # used to calculate the average of an array +using SNOW # the sparse nonlinear optimization wrapper that provides a friendly interface for these types of large evaluation problems + +runpath = splitdir(@__FILE__)[1] # This path variable ensures that you can invoke this script from anywhere and the program will know where this file is and the subsequent dependent files like airfoil polars, etc. + +# This is an example objective and constraint function, which passes by reference in the constraint array that gets mutated by the function, while the variables are the design inputs from the optimizer. +# The return is simply the objective +function messyoptfun!(constraints,Vars) + + OWENS_Options = OWENS.MasterInput("$runpath/modeling_options_OWENS_windioExample.yml") + # These options are the OWENS specific runtime options, as opposed to the design options coming from the WindIO + + WINDIO_filename = "$runpath/WINDIO_example.yaml" + windio = YAML.load_file(WINDIO_filename; dicttype=OrderedCollections.OrderedDict{Symbol,Any}) + # The windio filename can be passed into the runtime function below, or you can read the yaml and mutate it directly here to bypass filereading. + # It is planned to have all aspects of the WINDIO design details incorporated as the main input method to OWENS. + # However, due to the complexity of the transition, the airfoil polars, geometry, and composite layup information and material properties are still in work + + + # Design Variables, here are three examples of possible inputs for a constant RPM simulation. + quarter_span_radius = Vars[1]#24.0 + max_radius = Vars[2]#42.0 + RPM = Vars[3]#25.0 + + # Additional design variables recommended for initial point design + # chord control points + # composite thickness control points + # twist offset control points + + # Additional design varibles recommended for other critical DLCs (parked and emergency shutdown) + + # Since we are using constant RPM and there isn't a constant RPM option in the WindIO control block, it is within the OWENS Options + OWENS_Options.RPM = RPM + + # Now, rather than waste dozens of design variables on the overall shape of the blade, take the two control points and spline them to a full definition + # Note that splining at this level gives you more control, but the same thing happens internally, so you could specify the sparse control points and it will do this for you. + x_control_pts = [0.0,quarter_span_radius,max_radius,quarter_span_radius,0.0] + x_control_pts_grid = [0.0,0.25,0.5,0.75,1.0] + + x_grid = windio[:components][:blade][:internal_structure_2d_fem][:reference_axis][:x][:grid] + x_values = FLOWMath.akima(x_control_pts_grid,x_control_pts,x_grid) + + windio[:components][:blade][:internal_structure_2d_fem][:reference_axis][:x][:values] = x_values + + # Run with the WindIO standard, which as mentioned before, is in progress to include all of the design components. + OWENS.runOWENSWINDIO(windio,OWENS_Options,runpath) + + # Read in all of the current OWENS outputs from the run. This is a portion of what is calculated internally. + file = "$runpath/InitialDataOutputs.h5" + t = HDF5.h5read(file,"t") # Array of time that the simulation was run at + aziHist = HDF5.h5read(file,"aziHist") # Array of azimuthal positions for each time + OmegaHist = HDF5.h5read(file,"OmegaHist") # Array of rotational rates at each time + OmegaDotHist = HDF5.h5read(file,"OmegaDotHist") # Array of rotational acceleration at each time + gbHist = HDF5.h5read(file,"gbHist") # if active, gearbox model azimuthal position + gbDotHist = HDF5.h5read(file,"gbDotHist") # if active, gearbox model rotational speed + gbDotDotHist = HDF5.h5read(file,"gbDotDotHist") # if active, gearbox model rotational acceleration + FReactionHist = HDF5.h5read(file,"FReactionHist") # array sized (N_timesteps,NDOF) of reaction forces where each DOF is aligned with the mesh nodes, so first node is values 1:6, second is 7:12, hub FOR x,y,z, mx,my,mz forces and moments + FTwrBsHist = HDF5.h5read(file,"FTwrBsHist") # if running floating, gives the tower base forces and moments + genTorque = HDF5.h5read(file,"genTorque") # if generator model active, history of generator torque + genPower = HDF5.h5read(file,"genPower") # if generator model active, history of generator power + torqueDriveShaft = HDF5.h5read(file,"torqueDriveShaft") # if drivetrain model active, driveshaft torque + uHist = HDF5.h5read(file,"uHist") # displacement history sized (N_timesteps, NDOF), maps to the mesh nodes similarly to FReactionHist + uHist_prp = HDF5.h5read(file,"uHist_prp") # if active, platform displacement history + epsilon_x_hist = HDF5.h5read(file,"epsilon_x_hist") # beam strain along the span for each element in the mesh, sized (NQuadPoints,N_Elements,N_timesteps) + epsilon_y_hist = HDF5.h5read(file,"epsilon_y_hist") # beam strain in the chorwise direction for each element in the mesh, sized (NQuadPoints,N_Elements,N_timesteps) + epsilon_z_hist = HDF5.h5read(file,"epsilon_z_hist") # beam strain in the chord thickness direction for each element in the mesh, sized (NQuadPoints,N_Elements,N_timesteps) + kappa_x_hist = HDF5.h5read(file,"kappa_x_hist") # beam curvature about spanwise direction (twist) for each element in the mesh, sized (NQuadPoints,N_Elements,N_timesteps) + kappa_y_hist = HDF5.h5read(file,"kappa_y_hist") # beam curvature about the chordwise direction (flap) for each element in the mesh, sized (NQuadPoints,N_Elements,N_timesteps) + kappa_z_hist = HDF5.h5read(file,"kappa_z_hist") # beam curvature about the chord thickness direction (lag) for each element in the mesh, sized (NQuadPoints,N_Elements,N_timesteps) + massOwens = HDF5.h5read(file,"massOwens") # integral mass of the composite structures + stress_U = HDF5.h5read(file,"stress_U") # composite stress of the nominal low pressure side of the blade in the upper laminate, sized (N_timesteps,N_composite_input_stations,N_chordwise_input_stations, (principal,transverse, shear)) + SF_ult_U = HDF5.h5read(file,"SF_ult_U") # ultimate safety factor for the specified failure model, size(N_timesteps,N_composite_input_stations,N_chordwise_input_stations) + SF_buck_U = HDF5.h5read(file,"SF_buck_U") # simple buckling safety factor, size(N_timesteps,N_composite_input_stations,N_chordwise_input_stations) + stress_L = HDF5.h5read(file,"stress_L") # for blade lower surface, same as upper + SF_ult_L = HDF5.h5read(file,"SF_ult_L") # for blade lower surface, same as upper + SF_buck_L = HDF5.h5read(file,"SF_buck_L") # for blade lower surface, same as upper + stress_TU = HDF5.h5read(file,"stress_TU") # for tower upper surface, same format as blade + SF_ult_TU = HDF5.h5read(file,"SF_ult_TU") # for tower upper surface, same format as blade + SF_buck_TU = HDF5.h5read(file,"SF_buck_TU") # for tower upper surface, same format as blade + stress_TL = HDF5.h5read(file,"stress_TL") # for tower lower surface, same format as blade + SF_ult_TL = HDF5.h5read(file,"SF_ult_TL") # for tower lower surface, same format as blade + SF_buck_TL = HDF5.h5read(file,"SF_buck_TL") # for tower lower surface, same format as blade + topstrainout_blade_U = HDF5.h5read(file,"topstrainout_blade_U") # strain in the composite frame of reference, for upper side of blade, sized (N_timesteps,N_composite_input_stations,N_chordwise_input_stations, (principal,transverse, shear, beam strain x,beam strain y,beam strain z,beam curvature x,beam curvature y,beam curvature z)) + topstrainout_blade_L = HDF5.h5read(file,"topstrainout_blade_L") # same as above, but for blade lower + topstrainout_tower_U = HDF5.h5read(file,"topstrainout_tower_U") # same as above, but for lower upper surface + topstrainout_tower_L = HDF5.h5read(file,"topstrainout_tower_L") # same as above, but for lower upper surface + topDamage_blade_U = HDF5.h5read(file,"topDamage_blade_U") # for the blade upper miner's damage accumulated for the simulated time, in the worst case ply, size (N_composite_input_stations,N_chordwise_input_stations) + topDamage_blade_L = HDF5.h5read(file,"topDamage_blade_L") # for the blade lower, like above + topDamage_tower_U = HDF5.h5read(file,"topDamage_tower_U") # for the tower upper, like above + topDamage_tower_L = HDF5.h5read(file,"topDamage_tower_L") # for the tower lower, like above + + # Formulate our objective function to be a pseudo LCOE. You should consider scaling your outputs to achieve well scaled gradients + power = (mean(-FReactionHist[:,6])*(RPM*2*pi/60)) + pseudoLCOE = massOwens/power + + # Constraints on the minimum allowable safety factor, the minimum allowable lifetime damage, and that the power must be greater than 0.0 so the optimizer doesn't invert the LCOE equation. + minSF = FLOWMath.ksmin(SF_ult_U) + println(FLOWMath.ksmax(topDamage_blade_U)) + maxFatiguePer20yr = FLOWMath.ksmax(topDamage_blade_U/t[end]*60*60*20*365*24,1e10) + + constraints[1] = 1.0 - minSF # 1.0,1,# of stacks ->,7,Stack ID ->,1,2,3,4,5,6,7,Segment ID ->,1,2,3,4,5,6,7,8,9,10,11,12,DP Types,1,2,3,4,5,6,7,8,9,10,11,12,1,2,3,4,5,6,7,8,9,10,11,12,, +,,,,,,# of segments ->,12,Material ID ->,1,2,4,1,1,2,4,,,,,,,,,,,,,,,,,,,,,,,,,,,first entry in the CSV list is the exterior blade surface stack,,,,,,,,,,,,SW1, +Sta.#,Blade span (m),Airfoil Shape File,TE Type,Twist (deg),Chord,xoffset,aero center,Section Label,LE,Panel_Face,Panel_Core,Spar,TE,SW_Face,SW_Core,-blank-,HP_TE,HP_Aft_Panel,HP_Aft_Spar,HP_Fore_Spar,HP_Fore_Panel,HP_LE,LP_LE,LP_Fore_Panel,LP_Aft_Spar,LP_Fore_Spar,LP_Aft_Panel,LP_TE,,,,,,,,,,,,,,HP_TE,HP_Aft_Panel,HP_Aft_Spar,HP_Fore_Spar,HP_Fore_Panel,HP_LE,LP_LE,LP_Fore_Panel,LP_Aft_Spar,LP_Fore_Spar,LP_Aft_Panel,LP_TE,stacks,dps +1,0,NACA_0018,sharp,0,1.2,0.3,0.2,,12,1,8,12,12,0,0,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +2,4.1789,NACA_0018,sharp,0,1.2,0.3,0.2,,12,1,9,13,12,0,0,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +3,8.3578,NACA_0018,sharp,0,1.2,0.3,0.2,,12,1,9,13,12,0,0,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +4,12.5367,NACA_0018,sharp,0,1.2,0.3,0.2,,11,1,8,12,11,0,0,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +5,16.7156,NACA_0018,sharp,0,1.2,0.3,0.2,,9,1,7,10,9,0,0,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +6,20.8945,NACA_0018,sharp,0,1.2,0.3,0.2,,8,1,6,8,8,0,0,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +7,25.0734,NACA_0018,sharp,0,1.2,0.3,0.2,,8,1,6,8,8,0,0,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +8,29.2523,NACA_0018,sharp,0,1.2,0.3,0.2,,9,1,7,10,9,0,0,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +9,33.4312,NACA_0018,sharp,0,1.2,0.3,0.2,,11,1,8,12,11,0,0,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +10,37.6101,NACA_0018,sharp,0,1.2,0.3,0.2,,12,1,9,13,12,0,0,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +11,41.9,NACA_0018,sharp,0,1.2,0.3,0.2,,12,1,9,13,12,0,0,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" diff --git a/examples/helical_riverine/GeomBlades_AD.csv b/examples/helical_riverine/GeomBlades_AD.csv deleted file mode 100644 index c05de7e3..00000000 --- a/examples/helical_riverine/GeomBlades_AD.csv +++ /dev/null @@ -1,33 +0,0 @@ -SNL_34m_Aluminum,,,,# Shear webs ->,11,# of stacks ->,6,Stack ID ->,1,2,3,4,5,6,Segment ID ->,1,2,3,4,5,6,7,8,9,10,11,12,13,14,15,16,17,18,19,20,21,22,23,24,DP Types,1,2,3,4,5,6,7,8,9,10,11,12,13,14,15,16,17,18,19,20,21,22,23,24,1,2,3,4,5,6,7,8,9,10,11,12,13,14,15,16,17,18,19,20,21,22,23,24,,,,,,,,,,,,,,,,,,,,,, -,,,,,,# of segments ->,24,Material ID ->,1,2,3,4,5,6,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,first entry in the CSV list is the exterior blade surface stack,,,,,,,,,,,,,,,,,,,,,,,,SW1,,SW2,,SW3,,SW4,,SW5,,SW6,,SW7,,SW8,,SW9,,SW10,,SW11, -Sta.#,Blade span (m),Airfoil Shape File,TE Type,Twist (deg),Chord,xoffset,aero center,Section Label,Base Skin and Rib,Mid Skin,Zero,Rib Mid,Rib Center,Center Skin,-blank-,HPBay12,HPBay11,HPBay10,HPBay9,HPBay8,HPBay7,HPBay6,HPBay5,HPBay4,HPBay3,HPBay2,HPBay1,LPBay1,LPBay2,LPBay3,LPBay4,LPBay5,LPBay6,LPBay7,LPBay8,LPBay9,LPBay10,LPBay11,LPBay12,,,,,,,,,,,,,,,,,,,,,,,,,,HPBay12,HPBay11,HPBay10,HPBay9,HPBay8,HPBay7,HPBay6,HPBay5,HPBay4,HPBay3,HPBay2,HPBay1,LPBay1,LPBay2,LPBay3,LPBay4,LPBay5,LPBay6,LPBay7,LPBay8,LPBay9,LPBay10,LPBay11,LPBay12,stacks,dps,stacks,,,,,,,,,,,,,,,,,,, -1,0,NACA_0018,sharp,0,1.219,0.3,0.25,R,1,0,0,0,0,0,-1,-0.9167,-0.8333,-0.75,-0.6667,-0.5833,-0.5,-0.4167,-0.3333,-0.25,-0.1667,-0.0833,0,0.0833,0.1667,0.25,0.3333,0.4167,0.5,0.5833,0.6667,0.75,0.8333,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","13,11,11,13","1,","14,10,10,14","1,","15,9,9,15","1,","16,8,8,16","1,","17,7,7,17","1,","18,6,6,18","1,","19,5,5,19","1,","20,4,4,20","1,","21,3,3,21","1,","22,2,2,22","1,","23,1,1,23" -2,3.672615101,NACA_0018,sharp,0,1.219,0.3,0.25,R,1,0,0,0,0,0,-1,-0.9167,-0.8333,-0.75,-0.6667,-0.5833,-0.5,-0.4167,-0.3333,-0.25,-0.1667,-0.0833,0,0.0833,0.1667,0.25,0.3333,0.4167,0.5,0.5833,0.6667,0.75,0.8333,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","13,11,11,13","1,","14,10,10,14","1,","15,9,9,15","1,","16,8,8,16","1,","17,7,7,17","1,","18,6,6,18","1,","19,5,5,19","1,","20,4,4,20","1,","21,3,3,21","1,","22,2,2,22","1,","23,1,1,23" -3,7.344285215,NACA_0018,sharp,0,1.219,0.3,0.25,R,1,0,0,0,0,0,-1,-0.9167,-0.8333,-0.75,-0.6667,-0.5833,-0.5,-0.4167,-0.3333,-0.25,-0.1667,-0.0833,0,0.0833,0.1667,0.25,0.3333,0.4167,0.5,0.5833,0.6667,0.75,0.8333,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","13,11,11,13","1,","14,10,10,14","1,","15,9,9,15","1,","16,8,8,16","1,","17,7,7,17","1,","18,6,6,18","1,","19,5,5,19","1,","20,4,4,20","1,","21,3,3,21","1,","22,2,2,22","1,","23,1,1,23" -4,10.89367149,NACA_0018,sharp,0,1.219,0.3,0.25,RT,1,0,0,0,0,0,-1,-0.9167,-0.8333,-0.75,-0.6667,-0.5833,-0.5,-0.4167,-0.3333,-0.25,-0.1667,-0.0833,0,0.0833,0.1667,0.25,0.3333,0.4167,0.5,0.5833,0.6667,0.75,0.8333,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","13,11,11,13","1,","14,10,10,14","1,","15,9,9,15","1,","16,8,8,16","1,","17,7,7,17","1,","18,6,6,18","1,","19,5,5,19","1,","20,4,4,20","1,","21,3,3,21","1,","22,2,2,22","1,","23,1,1,23" -5,10.9717051,NACA_0018,sharp,0,1.067,0.3,0.25,T,0,1,0,1,0,0,-1,-0.9167,-0.9,-0.8,-0.7,-0.6,-0.5,-0.4,-0.3,-0.2,-0.1,-0.0833,0,0.0833,0.1,0.2,0.3,0.4,0.5,0.6,0.7,0.8,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","4,","14,10,10,14","4,","15,9,9,15","4,","16,8,8,16","4,","17,7,7,17","4,","18,6,6,18","4,","19,5,5,19","4,","20,4,4,20","4,","21,3,3,21","4,","22,2,2,22","3,","22,2,2,22","3,","23,1,1,23" -6,13.87890492,NACA_0018,sharp,0,1.067,0.3,0.25,T,0,1,0,1,0,0,-1,-0.9167,-0.9,-0.8,-0.7,-0.6,-0.5,-0.4,-0.3,-0.2,-0.1,-0.0833,0,0.0833,0.1,0.2,0.3,0.4,0.5,0.6,0.7,0.8,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","4,","14,10,10,14","4,","15,9,9,15","4,","16,8,8,16","4,","17,7,7,17","4,","18,6,6,18","4,","19,5,5,19","4,","20,4,4,20","4,","21,3,3,21","4,","22,2,2,22","3,","22,2,2,22","3,","23,1,1,23" -7,16.58070907,NACA_0018,sharp,0,1.067,0.3,0.25,T,0,1,0,1,0,0,-1,-0.9167,-0.9,-0.8,-0.7,-0.6,-0.5,-0.4,-0.3,-0.2,-0.1,-0.0833,0,0.0833,0.1,0.2,0.3,0.4,0.5,0.6,0.7,0.8,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","4,","14,10,10,14","4,","15,9,9,15","4,","16,8,8,16","4,","17,7,7,17","4,","18,6,6,18","4,","19,5,5,19","4,","20,4,4,20","4,","21,3,3,21","4,","22,2,2,22","3,","22,2,2,22","3,","23,1,1,23" -8,18.16034582,NACA_0018,sharp,0,1.067,0.3,0.25,TC,0,1,0,1,0,0,-1,-0.9167,-0.9,-0.8,-0.7,-0.6,-0.5,-0.4,-0.3,-0.2,-0.1,-0.0833,0,0.0833,0.1,0.2,0.3,0.4,0.5,0.6,0.7,0.8,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","4,","14,10,10,14","4,","15,9,9,15","4,","16,8,8,16","4,","17,7,7,17","4,","18,6,6,18","4,","19,5,5,19","4,","20,4,4,20","4,","21,3,3,21","4,","22,2,2,22","3,","22,2,2,22","3,","23,1,1,23" -9,18.21843304,NACA_0018,sharp,0,0.914,0.3,0.25,C,0,0,0,0,1,1,-1,-0.9167,-0.9,-0.875,-0.75,-0.625,-0.5,-0.375,-0.25,-0.125,-0.1,-0.0833,0,0.0833,0.1,0.125,0.25,0.375,0.5,0.625,0.75,0.875,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","5,","15,9,9,15","5,","16,8,8,16","5,","17,7,7,17","5,","18,6,6,18","5,","19,5,5,19","5,","20,4,4,20","5,","21,3,3,21","3,","18,2,2,18","3,","19,1,1,19","3,","22,2,2,22","3,","23,1,1,23" -10,19.02368414,NACA_0018,sharp,0,0.914,0.3,0.25,C,0,0,0,0,1,1,-1,-0.9167,-0.9,-0.875,-0.75,-0.625,-0.5,-0.375,-0.25,-0.125,-0.1,-0.0833,0,0.0833,0.1,0.125,0.25,0.375,0.5,0.625,0.75,0.875,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","5,","15,9,9,15","5,","16,8,8,16","5,","17,7,7,17","5,","18,6,6,18","5,","19,5,5,19","5,","20,4,4,20","5,","21,3,3,21","3,","18,2,2,18","3,","19,1,1,19","3,","22,2,2,22","3,","23,1,1,23" -11,21.25293416,NACA_0018,sharp,0,0.914,0.3,0.25,C,0,0,0,0,1,1,-1,-0.9167,-0.9,-0.875,-0.75,-0.625,-0.5,-0.375,-0.25,-0.125,-0.1,-0.0833,0,0.0833,0.1,0.125,0.25,0.375,0.5,0.625,0.75,0.875,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","5,","15,9,9,15","5,","16,8,8,16","5,","17,7,7,17","5,","18,6,6,18","5,","19,5,5,19","5,","20,4,4,20","5,","21,3,3,21","3,","18,2,2,18","3,","19,1,1,19","3,","22,2,2,22","3,","23,1,1,23" -12,23.36835879,NACA_0018,sharp,0,0.914,0.3,0.25,C,0,0,0,0,1,1,-1,-0.9167,-0.9,-0.875,-0.75,-0.625,-0.5,-0.375,-0.25,-0.125,-0.1,-0.0833,0,0.0833,0.1,0.125,0.25,0.375,0.5,0.625,0.75,0.875,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","5,","15,9,9,15","5,","16,8,8,16","5,","17,7,7,17","5,","18,6,6,18","5,","19,5,5,19","5,","20,4,4,20","5,","21,3,3,21","3,","18,2,2,18","3,","19,1,1,19","3,","22,2,2,22","3,","23,1,1,23" -13,25.41318676,NACA_0018,sharp,0,0.914,0.3,0.25,C,0,0,0,0,1,1,-1,-0.9167,-0.9,-0.875,-0.75,-0.625,-0.5,-0.375,-0.25,-0.125,-0.1,-0.0833,0,0.0833,0.1,0.125,0.25,0.375,0.5,0.625,0.75,0.875,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","5,","15,9,9,15","5,","16,8,8,16","5,","17,7,7,17","5,","18,6,6,18","5,","19,5,5,19","5,","20,4,4,20","5,","21,3,3,21","3,","18,2,2,18","3,","19,1,1,19","3,","22,2,2,22","3,","23,1,1,23" 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ID,,,[mm],[MPa],[MPa],[MPa],[MPa],[MPa],[MPa],[-],[-],[-],[kg/m3],[MPa],[MPa],[MPa],[MPa],[MPa],[MPa],[$/kg],,, +1,CLA_5500,orthotropic,0.66,98240,5102,5102,4274,4274,4274,0.3,0.3,0.3,1540,875.634139,-592.949102,100,100,100,100,2.06,CLA_5500,, +2,CBX_2400,orthotropic,0.81,14931,14931,5102,23890,4274,4274,0.3,0.3,0.3,1530,455.053962,-455.053962,100,100,100,100,2.10,CBX_2400,, +3,ETLX_2400,orthotropic,0.66,20333,9305,9305,4756,4756,4756,0.3,0.3,0.3,1900,530.896289,-530.896289,100,100,100,100,2.21,ETLX_2400,, +4,Airex_C70_55,orthotropic,1,45,45,69,22,22,22,0.2,0.2,0.2,59,100,100,100,100,100,100,7.23,Airex_C70_55,, +5,EBX_2400_x10,orthotropic,0.07,982400,51020,51020,42740,42740,42740,0.3,0.3,0.3,15300,4550.53962,-4550.53962,100,100,100,100,2.06,EBX_2400_x10,, +6,ETLX_2400_x10,orthotropic,0.08,149310,149310,51020,238900,42740,42740,0.3,0.3,0.3,19000,5308.96289,-5308.96289,100,100,100,100,2.10,ETLX_2400_x10,, +7,Airex_C70_55_x10,orthotropic,0.07,203335,93051,93051,47560,47560,47560,0.2,0.2,0.2,590,100,100,100,100,100,100,7.23,Airex_C70_55_x10,, +8,CFP-baseline,orthotropic,0.66,157600,9100,9100,3300,3300,3300,0.263,0.263,0.35,1600,2236,-1528,100,100,100,100,16.44,CFP-baseline,, \ No newline at end of file diff --git a/examples/helical_riverine/NuMAD_SNL34mMaterials.csv b/examples/helical_riverine/NuMAD_SNL34mMaterials.csv deleted file mode 100644 index e5aff4cb..00000000 --- a/examples/helical_riverine/NuMAD_SNL34mMaterials.csv +++ /dev/null @@ -1,9 +0,0 @@ -,,,,Ex,Ey,Ez,Gxy,Gyz,Gxz,prxy,pryz,prxz,,,, -,,Type,Layer Thickness,E11,E22,,G12,,,nu12,,,density,UTSx,UCSx,UTSy,UCSy,UTSz,UCSz,Cost,Reference,, -Material ID,,,[mm],[MPa],[MPa],[MPa],[MPa],[MPa],[MPa],[-],[-],[-],[kg/m3],[MPa],[MPa],[MPa],[MPa],[MPa],[MPa],[$/kg],,, -1,Aluminum_6063_T6_R,isotropic,8.087738693,6.89E+04,6.89E+04,6.89E+04,2.58E+04,2.58E+04,2.58E+04,0.33,0.33,0.33,2700,241,434,100,100,100,100,3.00,Base Skin and Web -2,Aluminum_6063_T6_T&C,isotropic,4.619000542,6.89E+04,6.89E+04,6.89E+04,2.58E+04,2.58E+04,2.58E+04,0.33,0.33,0.33,2700,241,434,100,100,100,100,3.00,Mid Skin -3,Aluminum_6063_T6_zero,isotropic,0,6.89E+04,6.89E+04,6.89E+04,2.58E+04,2.58E+04,2.58E+04,0.33,0.33,0.33,2700,241,434,100,100,100,100,3.00,"For numerical ease, include webs etc everywhere, just set thickness to zero" -4,Aluminum_6063_T6_T&C,isotropic,9.003307364,6.89E+04,6.89E+04,6.89E+04,2.58E+04,2.58E+04,2.58E+04,0.33,0.33,0.33,2700,241,434,100,100,100,100,3.00,Rib Mid -5,Aluminum_6063_T6_T&C,isotropic,9.563734009,6.89E+04,6.89E+04,6.89E+04,2.58E+04,2.58E+04,2.58E+04,0.33,0.33,0.33,2700,241,434,100,100,100,100,3.00,Rib Center -6,Aluminum_6063_T6_T&C,isotropic,4.806055859,6.89E+04,6.89E+04,6.89E+04,2.58E+04,2.58E+04,2.58E+04,0.33,0.33,0.33,2700,241,434,100,100,100,100,3.00,Center Skin diff --git a/examples/helical_riverine/TowerGeom.csv b/examples/helical_riverine/TowerGeom.csv index 91a80bc2..1663c19d 100644 --- a/examples/helical_riverine/TowerGeom.csv +++ b/examples/helical_riverine/TowerGeom.csv @@ -11,7 +11,7 @@ Sta.#,Blade span (m),Airfoil Shape File,TE Type,Twist (deg),Chord,xoffset,aero c 8,29.2523,circular,round,0,2,0.5,0.25,,24.000,1.000,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, 9,33.4312,circular,round,0,2,0.5,0.25,,24.000,1.000,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, 10,37.6101,circular,round,0,2,0.5,0.25,,24.000,1.000,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, -11,41.789,circular,round,0,2,0.5,0.25,,24.000,1.000,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, +11,41.9,circular,round,0,2,0.5,0.25,,24.000,1.000,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, ,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, ,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, ,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, diff --git a/examples/helical_riverine/airfoils/NACA_0018.dat b/examples/helical_riverine/airfoils/NACA_0018.dat index 79f75ece..e4b94c5a 100644 --- a/examples/helical_riverine/airfoils/NACA_0018.dat +++ b/examples/helical_riverine/airfoils/NACA_0018.dat @@ -1,1096 +1,1464 @@ -Title: NACA0018 -Thickness to Chord Ratio: 0.18 -Zero Lift AOA (deg): 0 -Reverse Camber Direction: 0 - -Reynolds Number: 1.00e4 -BV Dyn. Stall Model - Positive Stall AOA (deg): 1 -BV Dyn. Stall Model - Negative Stall AOA (deg): -1 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 3.478 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1 -AOA (deg) CL CD Cm25 --180 0 0 0 --175 0.66 0.055 0 --170 0.85 0.14 0 --165 0.68 0.23 0 --160 0.635 0.32 0 --155 0.67 0.42 0 --150 0.77 0.575 0 --145 0.9 0.755 0 --140 0.98 0.925 0 --135 0.93 1.085 0 --130 0.85 1.225 0 --125 0.76 1.35 0 --120 0.67 1.465 0 --115 0.575 1.555 0 --110 0.45 1.635 0 --105 0.32 1.7 0 --100 0.185 1.75 0 --95 0.05 1.78 0 --90 -0.09 1.8 0 --85 -0.23 1.8 0 --80 -0.365 1.78 0 --75 -0.5 1.735 0 --70 -0.63 1.665 0 --65 -0.76 1.575 0 --60 -0.875 1.47 0 --55 -0.955 1.345 0 --50 -1.02 1.215 0 --45 -1.05 1.075 0 --40 -1.035 0.92 0 --35 -0.98 0.745 0 --30 -0.855 0.57 0 --25 -0.5775 0.405 0 --22 -0.4172 0.329 0 --20 -0.3111 0.282 0 --18 -0.207 0.238 0 --16 -0.1051 0.196 0 --14 -0.0085 0.158 0 --12 0.0767 0.123 0 --11 0.1125 0.08 0 --10 0.1423 0.0574 0 --9 0.1584 0.0525 0 --8 0.1501 0.0489 0 --7 0.1182 0.0463 0 --6 0.0839 0.0443 0 --5 0.0577 0.0425 0 --4 0.0368 0.041 0 --3 0.0233 0.0399 0 --2 0.0154 0.0391 0 --1 0.0045 0.0387 0 -0 0 0.0385 0 -1 -0.0045 0.0387 0 -2 -0.0154 0.0391 0 -3 -0.0233 0.0399 0 -4 -0.0368 0.041 0 -5 -0.0577 0.0425 0 -6 -0.0839 0.0443 0 -7 -0.1182 0.0463 0 -8 -0.1501 0.0489 0 -9 -0.1584 0.0525 0 -10 -0.1423 0.0574 0 -11 -0.1125 0.08 0 -12 -0.0767 0.123 0 -14 0.0085 0.158 0 -16 0.1051 0.196 0 -18 0.207 0.238 0 -20 0.3111 0.282 0 -22 0.4172 0.329 0 -25 0.5775 0.405 0 -30 0.855 0.57 0 -35 0.98 0.745 0 -40 1.035 0.92 0 -45 1.05 1.075 0 -50 1.02 1.215 0 -55 0.955 1.345 0 -60 0.875 1.47 0 -65 0.76 1.575 0 -70 0.63 1.665 0 -75 0.5 1.735 0 -80 0.365 1.78 0 -85 0.23 1.8 0 -90 0.09 1.8 0 -95 -0.05 1.78 0 -100 -0.185 1.75 0 -105 -0.32 1.7 0 -110 -0.45 1.635 0 -115 -0.575 1.555 0 -120 -0.67 1.465 0 -125 -0.76 1.35 0 -130 -0.85 1.225 0 -135 -0.93 1.085 0 -140 -0.98 0.925 0 -145 -0.9 0.755 0 -150 -0.77 0.575 0 -155 -0.67 0.42 0 -160 -0.635 0.32 0 -165 -0.68 0.23 0 -170 -0.85 0.14 0 -175 -0.66 0.055 0 -180 0 0 0 - -Reynolds Number: 2.00e4 -BV Dyn. Stall Model - Positive Stall AOA (deg): 5 -BV Dyn. Stall Model - Negative Stall AOA (deg): -5 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 3.478 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 0.1788 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -0.1788 -AOA (deg) CL CD Cm25 --180 0 0.025 0 --175 0.66 0.055 0 --170 0.85 0.14 0 --165 0.68 0.23 0 --160 0.635 0.32 0 --155 0.67 0.42 0 --150 0.77 0.575 0 --145 0.9 0.755 0 --140 0.98 0.925 0 --135 0.93 1.085 0 --130 0.85 1.225 0 --125 0.76 1.35 0 --120 0.67 1.465 0 --115 0.575 1.555 0 --110 0.45 1.635 0 --105 0.32 1.7 0 --100 0.185 1.75 0 --95 0.05 1.78 0 --90 -0.09 1.8 0 --85 -0.23 1.8 0 --80 -0.365 1.78 0 --75 -0.5 1.735 0 --70 -0.63 1.665 0 --65 -0.76 1.575 0 --60 -0.875 1.47 0 --55 -0.955 1.345 0 --50 -1.02 1.21 0 --45 -1.05 1.075 0 --40 -1.035 0.92 0 --35 -0.98 0.745 0 --30 -0.855 0.57 0 --25 -0.5798 0.405 0 --22 -0.4198 0.329 0 --20 -0.3151 0.282 0 --18 -0.212 0.238 0 --16 -0.1114 0.196 0 --14 -0.0172 0.158 0 --12 0.0602 0.123 0 --10 0.1003 0.063 0 --9 0.0682 0.0396 0 --8 -0.0214 0.0376 0 --7 -0.1161 0.0358 0 --6 -0.1582 0.0339 0 --5 -0.1788 0.0323 0 --4 -0.1788 0.031 0 --3 -0.155 0.0299 0 --2 -0.1135 0.0292 0 --1 -0.0607 0.0288 0 -0 0 0.0286 0 -1 0.0607 0.0288 0 -2 0.1135 0.0292 0 -3 0.155 0.0299 0 -4 0.1788 0.031 0 -5 0.1788 0.0323 0 -6 0.1582 0.0339 0 -7 0.1161 0.0358 0 -8 0.0214 0.0376 0 -9 -0.0682 0.0396 0 -10 -0.1003 0.063 0 -12 -0.0602 0.123 0 -14 0.0172 0.158 0 -16 0.1114 0.196 0 -18 0.212 0.238 0 -20 0.3151 0.282 0 -22 0.4198 0.329 0 -25 0.5798 0.405 0 -30 0.855 0.57 0 -35 0.98 0.745 0 -40 1.035 0.92 0 -45 1.05 1.075 0 -50 1.02 1.21 0 -55 0.955 1.345 0 -60 0.875 1.47 0 -65 0.76 1.575 0 -70 0.63 1.665 0 -75 0.5 1.735 0 -80 0.365 1.78 0 -85 0.23 1.8 0 -90 0.09 1.8 0 -95 -0.05 1.78 0 -100 -0.185 1.75 0 -105 -0.32 1.7 0 -110 -0.45 1.635 0 -115 -0.575 1.555 0 -120 -0.67 1.465 0 -125 -0.76 1.35 0 -130 -0.85 1.225 0 -135 -0.93 1.085 0 -140 -0.98 0.925 0 -145 -0.9 0.755 0 -150 -0.77 0.575 0 -155 -0.67 0.42 0 -160 -0.635 0.32 0 -165 -0.68 0.23 0 -170 -0.85 0.14 0 -175 -0.66 0.055 0 -180 0 0.025 0 - -Reynolds Number: 4.00e4 -BV Dyn. Stall Model - Positive Stall AOA (deg): 7 -BV Dyn. Stall Model - Negative Stall AOA (deg): -7 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 5.363 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 0.4758 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -0.4758 -AOA (deg) CL CD Cm25 --180 0 0.025 0 --175 0.66 0.055 0 --170 0.85 0.14 0 --165 0.68 0.23 0 --160 0.635 0.32 0 --155 0.67 0.42 0 --150 0.77 0.575 0 --145 0.9 0.755 0 --140 0.98 0.925 0 --135 0.93 1.085 0 --130 0.85 1.225 0 --125 0.76 1.35 0 --120 0.67 1.465 0 --115 0.575 1.555 0 --110 0.45 1.635 0 --105 0.32 1.7 0 --100 0.185 1.75 0 --95 0.05 1.78 0 --90 -0.09 1.8 0 --85 -0.23 1.8 0 --80 -0.365 1.78 0 --75 -0.5 1.735 0 --70 -0.63 1.665 0 --65 -0.76 1.575 0 --60 -0.875 1.47 0 --55 -0.955 1.345 0 --50 -1.02 1.215 0 --45 -1.05 1.075 0 --40 -1.035 0.92 0 --35 -0.98 0.745 0 --30 -0.855 0.57 0 --25 -0.584 0.405 0 --22 -0.4265 0.329 0 --20 -0.3236 0.282 0 --18 -0.2228 0.238 0 --16 -0.1287 0.196 0 --14 -0.0489 0.158 0 --12 -0.0139 0.123 0 --10 -0.2108 0.062 0 --9 -0.3544 0.0327 0 --8 -0.4428 0.0303 0 --7 -0.4758 0.0282 0 --6 -0.4573 0.0263 0 --5 -0.4117 0.0247 0 --4 -0.3495 0.0235 0 --3 -0.2688 0.0225 0 --2 -0.1833 0.0219 0 --1 -0.0936 0.0215 0 -0 0 0.0214 0 -1 0.0936 0.0215 0 -2 0.1833 0.0219 0 -3 0.2688 0.0225 0 -4 0.3495 0.0235 0 -5 0.4117 0.0247 0 -6 0.4573 0.0263 0 -7 0.4758 0.0282 0 -8 0.4428 0.0303 0 -9 0.3544 0.0327 0 -10 0.2108 0.062 0 -12 0.0139 0.123 0 -14 0.0489 0.158 0 -16 0.1287 0.196 0 -18 0.2228 0.238 0 -20 0.3236 0.282 0 -22 0.4265 0.329 0 -25 0.584 0.405 0 -30 0.855 0.57 0 -35 0.98 0.745 0 -40 1.035 0.92 0 -45 1.05 1.075 0 -50 1.02 1.215 0 -55 0.955 1.345 0 -60 0.875 1.47 0 -65 0.76 1.575 0 -70 0.63 1.665 0 -75 0.5 1.735 0 -80 0.365 1.78 0 -85 0.23 1.8 0 -90 0.09 1.8 0 -95 -0.05 1.78 0 -100 -0.185 1.75 0 -105 -0.32 1.7 0 -110 -0.45 1.635 0 -115 -0.575 1.555 0 -120 -0.67 1.465 0 -125 -0.76 1.35 0 -130 -0.85 1.225 0 -135 -0.93 1.085 0 -140 -0.98 0.925 0 -145 -0.9 0.755 0 -150 -0.77 0.575 0 -155 -0.67 0.42 0 -160 -0.635 0.32 0 -165 -0.68 0.23 0 -170 -0.85 0.14 0 -175 -0.66 0.055 0 -180 0 0.025 0 - -Reynolds Number: 8.00e4 -BV Dyn. Stall Model - Positive Stall AOA (deg): 9 -BV Dyn. Stall Model - Negative Stall AOA (deg): -9 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 5.094 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 0.6606 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -0.6606 -AOA (deg) CL CD Cm25 --180 0 0.02 0 --175 0.66 0.055 0 --170 0.85 0.14 0 --165 0.68 0.23 0 --160 0.635 0.32 0 --155 0.67 0.42 0 --150 0.77 0.575 0 --145 0.9 0.755 0 --140 0.98 0.925 0 --135 0.93 1.085 0 --130 0.85 1.225 0 --125 0.76 1.35 0 --120 0.67 1.465 0 --115 0.575 1.555 0 --110 0.45 1.635 0 --105 0.32 1.7 0 --100 0.185 1.75 0 --95 0.05 1.78 0 --90 -0.09 1.8 0 --85 -0.23 1.8 0 --80 -0.365 1.78 0 --75 -0.5 1.735 0 --70 -0.63 1.665 0 --65 -0.76 1.575 0 --60 -0.875 1.47 0 --55 -0.955 1.345 0 --50 -1.02 1.215 0 --45 -1.05 1.075 0 --40 -1.035 0.92 0 --35 -0.98 0.745 0 --30 -0.855 0.57 0 --25 -0.5963 0.405 0 --22 -0.443 0.329 0 --20 -0.3472 0.282 0 --18 -0.2603 0.238 0 --16 -0.2027 0.196 0 --14 -0.2256 0.158 0 --12 -0.4408 0.08 0 --11 -0.5531 0.0315 0 --10 -0.6248 0.0288 0 --9 -0.6606 0.0264 0 --8 -0.6589 0.0242 0 --7 -0.6224 0.0223 0 --6 -0.5615 0.0206 0 --5 -0.4753 0.0192 0 --4 -0.388 0.0181 0 --3 -0.2924 0.0172 0 --2 -0.1935 0.0167 0 --1 -0.0889 0.0163 0 -0 0 0.0162 0 -1 0.0889 0.0163 0 -2 0.1935 0.0167 0 -3 0.2924 0.0172 0 -4 0.388 0.0181 0 -5 0.4753 0.0192 0 -6 0.5615 0.0206 0 -7 0.6224 0.0223 0 -8 0.6589 0.0242 0 -9 0.6606 0.0264 0 -10 0.6248 0.0288 0 -11 0.5531 0.0315 0 -12 0.4408 0.08 0 -14 0.2256 0.158 0 -16 0.2027 0.196 0 -18 0.2603 0.238 0 -20 0.3472 0.282 0 -22 0.443 0.329 0 -25 0.5963 0.405 0 -30 0.855 0.57 0 -35 0.98 0.745 0 -40 1.035 0.92 0 -45 1.05 1.075 0 -50 1.02 1.215 0 -55 0.955 1.345 0 -60 0.875 1.47 0 -65 0.76 1.575 0 -70 0.63 1.665 0 -75 0.5 1.735 0 -80 0.365 1.78 0 -85 0.23 1.8 0 -90 0.09 1.8 0 -95 -0.05 1.78 0 -100 -0.185 1.75 0 -105 -0.32 1.7 0 -110 -0.45 1.635 0 -115 -0.575 1.555 0 -120 -0.67 1.465 0 -125 -0.76 1.35 0 -130 -0.85 1.225 0 -135 -0.93 1.085 0 -140 -0.98 0.925 0 -145 -0.9 0.755 0 -150 -0.77 0.575 0 -155 -0.67 0.42 0 -160 -0.635 0.32 0 -165 -0.68 0.23 0 -170 -0.85 0.14 0 -175 -0.66 0.055 0 -180 0 0.02 0 - -Reynolds Number: 1.60e5 -BV Dyn. Stall Model - Positive Stall AOA (deg): 10 -BV Dyn. Stall Model - Negative Stall AOA (deg): -10 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.302 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 0.7949 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -0.7949 -AOA (deg) CL CD Cm25 --180 0 0.025 0 --175 0.66 0.055 0 --170 0.85 0.14 0 --165 0.68 0.23 0 --160 0.635 0.32 0 --155 0.67 0.42 0 --150 0.77 0.575 0 --145 0.9 0.755 0 --140 0.98 0.925 0 --135 0.93 1.085 0 --130 0.85 1.225 0 --125 0.76 1.35 0 --120 0.67 1.465 0 --115 0.575 1.555 0 --110 0.45 1.635 0 --105 0.32 1.7 0 --100 0.185 1.75 0 --95 0.05 1.78 0 --90 -0.09 1.8 0 --85 -0.23 1.8 0 --80 -0.365 1.78 0 --75 -0.5 1.735 0 --70 -0.63 1.665 0 --65 -0.76 1.575 0 --60 -0.875 1.47 0 --55 -0.955 1.345 0 --50 -1.02 1.215 0 --45 -1.05 1.075 0 --40 -1.035 0.92 0 --35 -0.98 0.745 0 --30 -0.855 0.57 0 --25 -0.6321 0.405 0 --22 -0.5026 0.329 0 --20 -0.4382 0.282 0 --18 -0.4202 0.238 0 --16 -0.4896 0.196 0 --14 -0.6237 0.158 0 --13 -0.6923 0.077 0 --12 -0.7488 0.0288 0 --11 -0.7852 0.0262 0 --10 -0.7949 0.0238 0 --9 -0.7781 0.0217 0 --8 -0.7373 0.0198 0 --7 -0.6724 0.0181 0 --6 -0.596 0.0166 0 --5 -0.5068 0.0153 0 --4 -0.4114 0.0144 0 --3 -0.3088 0.0137 0 --2 -0.22 0.0131 0 --1 -0.11 0.0129 0 -0 0 0.0128 0 -1 0.11 0.0129 0 -2 0.22 0.0131 0 -3 0.3088 0.0137 0 -4 0.4114 0.0144 0 -5 0.5068 0.0153 0 -6 0.596 0.0166 0 -7 0.6724 0.0181 0 -8 0.7373 0.0198 0 -9 0.7781 0.0217 0 -10 0.7949 0.0238 0 -11 0.7852 0.0262 0 -12 0.7488 0.0288 0 -13 0.6923 0.077 0 -14 0.6237 0.158 0 -16 0.4896 0.196 0 -18 0.4202 0.238 0 -20 0.4382 0.282 0 -22 0.5026 0.329 0 -25 0.6321 0.405 0 -30 0.855 0.57 0 -35 0.98 0.745 0 -40 1.035 0.92 0 -45 1.05 1.075 0 -50 1.02 1.215 0 -55 0.955 1.345 0 -60 0.875 1.47 0 -65 0.76 1.575 0 -70 0.63 1.665 0 -75 0.5 1.735 0 -80 0.365 1.78 0 -85 0.23 1.8 0 -90 0.09 1.8 0 -95 -0.05 1.78 0 -100 -0.185 1.75 0 -105 -0.32 1.7 0 -110 -0.45 1.635 0 -115 -0.575 1.555 0 -120 -0.67 1.465 0 -125 -0.76 1.35 0 -130 -0.85 1.225 0 -135 -0.93 1.085 0 -140 -0.98 0.925 0 -145 -0.9 0.755 0 -150 -0.77 0.575 0 -155 -0.67 0.42 0 -160 -0.635 0.32 0 -165 -0.68 0.23 0 -170 -0.85 0.14 0 -175 -0.66 0.055 0 -180 0 0.025 0 - -Reynolds Number: 3.60e5 -BV Dyn. Stall Model - Positive Stall AOA (deg): 12 -BV Dyn. Stall Model - Negative Stall AOA (deg): -12 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.302 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 0.9279 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -0.9279 -AOA (deg) CL CD Cm25 --180 0 0.025 0 --175 0.66 0.055 0 --170 0.85 0.14 0 --165 0.68 0.23 0 --160 0.635 0.32 0 --155 0.67 0.42 0 --150 0.77 0.575 0 --145 0.9 0.755 0 --140 0.98 0.925 0 --135 0.93 1.085 0 --130 0.85 1.225 0 --125 0.76 1.35 0 --120 0.67 1.465 0 --115 0.575 1.555 0 --110 0.45 1.635 0 --105 0.32 1.7 0 --100 0.185 1.75 0 --95 0.05 1.78 0 --90 -0.09 1.8 0 --85 -0.23 1.8 0 --80 -0.365 1.78 0 --75 -0.5 1.735 0 --70 -0.63 1.665 0 --65 -0.76 1.575 0 --60 -0.875 1.47 0 --55 -0.955 1.345 0 --50 -1.02 1.215 0 --45 -1.05 1.075 0 --40 -1.035 0.92 0 --35 -0.98 0.745 0 --30 -0.855 0.57 0 --25 -0.7724 0.405 0 --22 -0.705 0.329 0 --20 -0.6997 0.282 0 --18 -0.7319 0.238 0 --16 -0.8007 0.196 0 --14 -0.8803 0.094 0 --13 -0.9104 0.0259 0 --12 -0.9279 0.0235 0 --11 -0.9249 0.0213 0 --10 -0.8983 0.0194 0 --9 -0.8526 0.0176 0 --8 -0.7879 0.0159 0 --7 -0.71 0.0145 0 --6 -0.6228 0.0132 0 --5 -0.524 0.0121 0 --4 -0.44 0.0112 0 --3 -0.33 0.0107 0 --2 -0.22 0.0104 0 --1 -0.11 0.0102 0 -0 0 0.0101 0 -1 0.11 0.0102 0 -2 0.22 0.0104 0 -3 0.33 0.0107 0 -4 0.44 0.0112 0 -5 0.524 0.0121 0 -6 0.6228 0.0132 0 -7 0.71 0.0145 0 -8 0.7879 0.0159 0 -9 0.8526 0.0176 0 -10 0.8983 0.0194 0 -11 0.9249 0.0213 0 -12 0.9279 0.0235 0 -13 0.9104 0.0259 0 -14 0.8803 0.094 0 -16 0.8007 0.196 0 -18 0.7319 0.238 0 -20 0.6997 0.282 0 -22 0.705 0.329 0 -25 0.7724 0.405 0 -30 0.855 0.57 0 -35 0.98 0.745 0 -40 1.035 0.92 0 -45 1.05 1.075 0 -50 1.02 1.215 0 -55 0.955 1.345 0 -60 0.875 1.47 0 -65 0.76 1.575 0 -70 0.63 1.665 0 -75 0.5 1.735 0 -80 0.365 1.78 0 -85 0.23 1.8 0 -90 0.09 1.8 0 -95 -0.05 1.78 0 -100 -0.185 1.75 0 -105 -0.32 1.7 0 -110 -0.45 1.635 0 -115 -0.575 1.555 0 -120 -0.67 1.465 0 -125 -0.76 1.35 0 -130 -0.85 1.225 0 -135 -0.93 1.085 0 -140 -0.98 0.925 0 -145 -0.9 0.755 0 -150 -0.77 0.575 0 -155 -0.67 0.42 0 -160 -0.635 0.32 0 -165 -0.68 0.23 0 -170 -0.85 0.14 0 -175 -0.66 0.055 0 -180 0 0.025 0 - -Reynolds Number: 7.00e5 -BV Dyn. Stall Model - Positive Stall AOA (deg): 13 -BV Dyn. Stall Model - Negative Stall AOA (deg): -13 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.302 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.0289 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.0289 -AOA (deg) CL CD Cm25 --180 0 0.025 0 --175 0.66 0.055 0 --170 0.85 0.14 0 --165 0.68 0.23 0 --160 0.635 0.32 0 --155 0.67 0.42 0 --150 0.77 0.575 0 --145 0.9 0.755 0 --140 0.98 0.925 0 --135 0.93 1.085 0 --130 0.85 1.225 0 --125 0.76 1.35 0 --120 0.67 1.465 0 --115 0.575 1.555 0 --110 0.45 1.635 0 --105 0.32 1.7 0 --100 0.185 1.75 0 --95 0.5 1.78 0 --90 -0.09 1.8 0 --85 -0.23 1.8 0 --80 -0.365 1.78 0 --75 -0.5 1.735 0 --70 -0.63 1.665 0 --65 -0.76 1.575 0 --60 -0.875 1.47 0 --55 -0.955 1.345 0 --50 -1.02 1.215 0 --45 -1.05 1.075 0 --40 -1.035 0.92 0 --35 -0.98 0.745 0 --30 -0.855 0.57 0 --25 -0.9326 0.405 0 --22 -0.8867 0.329 0 --20 -0.8877 0.282 0 --18 -0.915 0.238 0 --16 -0.9648 0.196 0 --15 -0.9938 0.102 0 --14 -1.0175 0.0245 0 --13 -1.0289 0.0223 0 --12 -1.0245 0.0202 0 --11 -0.9973 0.0183 0 --10 -0.9541 0.0166 0 --9 -0.8904 0.015 0 --8 -0.8156 0.0136 0 --7 -0.7291 0.0123 0 --6 -0.6328 0.0112 0 --5 -0.55 0.0102 0 --4 -0.44 0.0096 0 --3 -0.33 0.0091 0 --2 -0.22 0.0088 0 --1 -0.11 0.0087 0 -0 0 0.0085 0 -1 0.11 0.0087 0 -2 0.22 0.0088 0 -3 0.33 0.0091 0 -4 0.44 0.0096 0 -5 0.55 0.0102 0 -6 0.6328 0.0112 0 -7 0.7291 0.0123 0 -8 0.8156 0.0136 0 -9 0.8904 0.015 0 -10 0.9541 0.0166 0 -11 0.9973 0.0183 0 -12 1.0245 0.0202 0 -13 1.0289 0.0223 0 -14 1.0175 0.0245 0 -15 0.9938 0.102 0 -16 0.9648 0.196 0 -18 0.915 0.238 0 -20 0.8877 0.282 0 -22 0.8867 0.329 0 -25 0.9326 0.405 0 -30 0.855 0.57 0 -35 0.98 0.745 0 -40 1.035 0.92 0 -45 1.05 1.075 0 -50 1.02 1.215 0 -55 0.955 1.345 0 -60 0.875 1.47 0 -65 0.76 1.575 0 -70 0.63 1.665 0 -75 0.5 1.735 0 -80 0.365 1.78 0 -85 0.23 1.8 0 -90 0.09 1.8 0 -95 -0.5 1.78 0 -100 -0.185 1.75 0 -105 -0.32 1.7 0 -110 -0.45 1.635 0 -115 -0.575 1.555 0 -120 -0.67 1.465 0 -125 -0.76 1.35 0 -130 -0.85 1.225 0 -135 -0.93 1.085 0 -140 -0.98 0.925 0 -145 -0.9 0.755 0 -150 -0.77 0.575 0 -155 -0.67 0.42 0 -160 -0.635 0.32 0 -165 -0.68 0.23 0 -170 -0.85 0.14 0 -175 -0.66 0.055 0 -180 0 0.025 0 - -Reynolds Number: 1.00e6 -BV Dyn. Stall Model - Positive Stall AOA (deg): 13 -BV Dyn. Stall Model - Negative Stall AOA (deg): -13 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.302 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.0804 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.0804 -AOA (deg) CL CD Cm25 --180 0 0.025 0 --175 0.66 0.055 0 --170 0.85 0.14 0 --165 0.68 0.23 0 --160 0.635 0.32 0 --155 0.67 0.42 0 --150 0.77 0.575 0 --145 0.9 0.755 0 --140 0.98 0.925 0 --135 0.93 1.085 0 --130 0.85 1.225 0 --125 0.76 1.35 0 --120 0.67 1.465 0 --115 0.575 1.555 0 --110 0.45 1.635 0 --105 0.32 1.7 0 --100 0.185 1.75 0 --95 0.05 1.78 0 --90 -0.09 1.8 0 --85 -0.23 1.8 0 --80 -0.365 1.78 0 --75 -0.5 1.735 0 --70 -0.63 1.665 0 --65 -0.76 1.575 0 --60 -0.875 1.47 0 --55 -0.955 1.345 0 --50 -1.02 1.215 0 --45 -1.05 1.075 0 --40 -1.035 0.92 0 --35 -0.98 0.745 0 --30 -0.855 0.57 0 --25 -1.0107 0.405 0 --22 -0.9696 0.329 0 --20 -0.9707 0.282 0 --18 -0.9959 0.238 0 --16 -1.0402 0.108 0 --15 -1.0624 0.0251 0 --14 -1.0793 0.0227 0 --13 -1.0804 0.0206 0 --12 -1.0664 0.0187 0 --11 -1.0284 0.017 0 --10 -0.9751 0.0154 0 --9 -0.9067 0.0139 0 --8 -0.8256 0.0126 0 --7 -0.7362 0.0115 0 --6 -0.66 0.0102 0 --5 -0.55 0.0095 0 --4 -0.44 0.0089 0 --3 -0.33 0.0086 0 --2 -0.22 0.0083 0 --1 -0.11 0.0082 0 -0 0 0.0082 0 -1 0.11 0.0082 0 -2 0.22 0.0083 0 -3 0.33 0.0086 0 -4 0.44 0.0089 0 -5 0.55 0.0095 0 -6 0.66 0.0102 0 -7 0.7362 0.0115 0 -8 0.8256 0.0126 0 -9 0.9067 0.0139 0 -10 0.9751 0.0154 0 -11 1.0284 0.017 0 -12 1.0664 0.0187 0 -13 1.0804 0.0206 0 -14 1.0793 0.0227 0 -15 1.0624 0.0251 0 -16 1.0402 0.108 0 -18 0.9959 0.238 0 -20 0.9707 0.282 0 -22 0.9696 0.329 0 -25 1.0107 0.405 0 -30 0.855 0.57 0 -35 0.98 0.745 0 -40 1.035 0.92 0 -45 1.05 1.075 0 -50 1.02 1.215 0 -55 0.955 1.345 0 -60 0.875 1.47 0 -65 0.76 1.575 0 -70 0.63 1.665 0 -75 0.5 1.735 0 -80 0.365 1.78 0 -85 0.23 1.8 0 -90 0.09 1.8 0 -95 -0.05 1.78 0 -100 -0.185 1.75 0 -105 -0.32 1.7 0 -110 -0.45 1.635 0 -115 -0.575 1.555 0 -120 -0.67 1.465 0 -125 -0.76 1.35 0 -130 -0.85 1.225 0 -135 -0.93 1.085 0 -140 -0.98 0.925 0 -145 -0.9 0.755 0 -150 -0.77 0.575 0 -155 -0.67 0.42 0 -160 -0.635 0.32 0 -165 -0.68 0.23 0 -170 -0.85 0.14 0 -175 -0.66 0.055 0 -180 0 0.025 0 - -Reynolds Number: 2.00e6 -BV Dyn. Stall Model - Positive Stall AOA (deg): 14 -BV Dyn. Stall Model - Negative Stall AOA (deg): -14 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.302 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.1813 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.1813 -AOA (deg) CL CD Cm25 --180 0 0.025 0 --175 0.66 0.055 0 --170 0.85 0.14 0 --165 0.68 0.23 0 --160 0.635 0.32 0 --155 0.67 0.42 0 --150 0.77 0.575 0 --145 0.9 0.755 0 --140 0.98 0.925 0 --135 0.93 1.085 0 --130 0.85 1.225 0 --125 0.76 1.35 0 --120 0.67 1.465 0 --115 0.575 1.555 0 --110 0.45 1.635 0 --105 0.32 1.7 0 --100 0.185 1.75 0 --95 0.05 1.78 0 --90 -0.09 1.8 0 --85 -0.23 1.8 0 --80 -0.365 1.78 0 --75 -0.5 0.735 0 --70 -0.63 1.665 0 --65 -0.76 1.575 0 --60 -0.875 1.47 0 --55 -0.955 1.345 0 --50 -1.02 1.215 0 --45 -1.05 1.075 0 --40 -1.035 0.92 0 --35 -0.98 0.745 0 --30 -0.855 0.57 0 --25 -1.1468 0.405 0 --22 -1.1127 0.329 0 --20 -1.1172 0.282 0 --18 -1.1383 0.238 0 --17 -1.155 0.12 0 --16 -1.1695 0.024 0 --15 -1.1813 0.0218 0 --14 -1.1813 0.0197 0 --13 -1.1662 0.0179 0 --12 -1.1296 0.0163 0 --11 -1.0772 0.01481 0 --10 -1.0111 0.0134 0 --9 -0.9314 0.0122 0 --8 -0.8439 0.0111 0 --7 -0.7449 0.0101 0 --6 -0.66 0.0093 0 --5 -0.55 0.0087 0 --4 -0.44 0.0084 0 --3 -0.33 0.008 0 --2 -0.22 0.0078 0 --1 -0.11 0.0077 0 -0 0 0.0077 0 -1 0.11 0.0077 0 -2 0.22 0.0078 0 -3 0.33 0.008 0 -4 0.44 0.0084 0 -5 0.55 0.0087 0 -6 0.66 0.0093 0 -7 0.7449 0.0101 0 -8 0.8439 0.0111 0 -9 0.9314 0.0122 0 -10 1.0111 0.0134 0 -11 1.0772 0.01481 0 -12 1.1296 0.0163 0 -13 1.1662 0.0179 0 -14 1.1813 0.0197 0 -15 1.1813 0.0218 0 -16 1.1695 0.024 0 -17 1.155 0.12 0 -18 1.1383 0.238 0 -20 1.1172 0.282 0 -22 1.1127 0.329 0 -25 1.1468 0.405 0 -30 0.855 0.57 0 -35 0.98 0.745 0 -40 1.035 0.92 0 -45 1.05 1.075 0 -50 1.02 1.215 0 -55 0.955 1.345 0 -60 0.875 1.47 0 -65 0.76 1.575 0 -70 0.63 1.665 0 -75 0.5 0.735 0 -80 0.365 1.78 0 -85 0.23 1.8 0 -90 0.09 1.8 0 -95 -0.05 1.78 0 -100 -0.185 1.75 0 -105 -0.32 1.7 0 -110 -0.45 1.635 0 -115 -0.575 1.555 0 -120 -0.67 1.465 0 -125 -0.76 1.35 0 -130 -0.85 1.225 0 -135 -0.93 1.085 0 -140 -0.98 0.925 0 -145 -0.9 0.755 0 -150 -0.77 0.575 0 -155 -0.67 0.42 0 -160 -0.635 0.32 0 -165 -0.68 0.23 0 -170 -0.85 0.14 0 -175 -0.66 0.055 0 -180 0 0.025 0 - -Reynolds Number: 5.00e6 -BV Dyn. Stall Model - Positive Stall AOA (deg): 16 -BV Dyn. Stall Model - Negative Stall AOA (deg): -16 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.302 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.3067 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.3067 -AOA (deg) CL CD Cm25 --180 0 0.025 0 --175 0.66 0.055 0 --170 0.85 0.14 0 --165 0.68 0.23 0 --160 0.635 0.32 0 --155 0.67 0.42 0 --150 0.77 0.575 0 --145 0.9 0.755 0 --140 0.98 0.925 0 --135 0.93 1.085 0 --130 0.85 1.225 0 --125 0.76 1.35 0 --120 0.67 1.465 0 --115 0.575 1.555 0 --110 0.45 1.635 0 --105 0.32 1.7 0 --100 0.185 1.75 0 --95 0.05 1.78 0 --90 -0.09 1.8 0 --85 -0.23 1.8 0 --80 -0.365 1.78 0 --75 -0.5 1.735 0 --70 -0.63 1.665 0 --65 -0.76 1.575 0 --60 -0.875 1.47 0 --55 -0.955 1.345 0 --50 -1.02 1.215 0 --45 -1.05 1.075 0 --40 -1.035 0.92 0 --35 -0.98 0.745 0 --30 -0.855 0.57 0 --25 -1.2925 0.405 0 --22 -1.2714 0.329 0 --20 -1.2768 0.282 0 --19 -1.2853 0.14 0 --18 -1.296 0.0244 0 --17 -1.3038 0.0223 0 --16 -1.3067 0.0203 0 --15 -1.3004 0.0185 0 --14 -1.2808 0.0168 0 --13 -1.243 0.0153 0 --12 -1.1884 0.014 0 --11 -1.1211 0.0128 0 --10 -1.0404 0.0117 0 --9 -0.9525 0.0108 0 --8 -0.8538 0.01 0 --7 -0.77 0.0093 0 --6 -0.66 0.0087 0 --5 -0.55 0.0083 0 --4 -0.44 0.0079 0 --3 -0.33 0.0077 0 --2 -0.22 0.0075 0 --1 -0.11 0.0073 0 -0 0 0.0073 0 -1 0.11 0.0073 0 -2 0.22 0.0075 0 -3 0.33 0.0077 0 -4 0.44 0.0079 0 -5 0.55 0.0083 0 -6 0.66 0.0087 0 -7 0.77 0.0093 0 -8 0.8538 0.01 0 -9 0.9525 0.0108 0 -10 1.0404 0.0117 0 -11 1.1211 0.0128 0 -12 1.1884 0.014 0 -13 1.243 0.0153 0 -14 1.2808 0.0168 0 -15 1.3004 0.0185 0 -16 1.3067 0.0203 0 -17 1.3038 0.0223 0 -18 1.296 0.0244 0 -19 1.2853 0.14 0 -20 1.2768 0.282 0 -22 1.2714 0.329 0 -25 1.2925 0.405 0 -30 0.855 0.57 0 -35 0.98 0.745 0 -40 1.035 0.92 0 -45 1.05 1.075 0 -50 1.02 1.215 0 -55 0.955 1.345 0 -60 0.875 1.47 0 -65 0.76 1.575 0 -70 0.63 1.665 0 -75 0.5 1.735 0 -80 0.365 1.78 0 -85 0.23 1.8 0 -90 0.09 1.8 0 -95 -0.05 1.78 0 -100 -0.185 1.75 0 -105 -0.32 1.7 0 -110 -0.45 1.635 0 -115 -0.575 1.555 0 -120 -0.67 1.465 0 -125 -0.76 1.35 0 -130 -0.85 1.225 0 -135 -0.93 1.085 0 -140 -0.98 0.925 0 -145 -0.9 0.755 0 -150 -0.77 0.575 0 -155 -0.67 0.42 0 -160 -0.635 0.32 0 -165 -0.68 0.23 0 -170 -0.85 0.14 0 -175 -0.66 0.055 0 -180 0 0.025 0 \ No newline at end of file +! ------------ AirfoilInfo v1.01.x Input File ---------------------------------- +! NACA 0018 at Re = 0.01,0.02,0.04,0.08,0.16,0.36,0.70,1,2,5 million +! line +! line +! ------------------------------------------------------------------------------ +DEFAULT InterpOrd - ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] +0.18 RelThickness - ! The non-dimensional thickness of the airfoil (thickness/chord) [only used if UAMod=7] [default=0.2] (-) +1 NonDimArea - ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) +@"NACA_0018_Coords.txt" NumCoords - ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +"NA" BL_file - ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. +10 NumTabs - ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. +! ------------------------------------------------------------------------------ +! data for table 1 +! ------------------------------------------------------------------------------ +0.01 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +8.136711569484852 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-8.136711569484852 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.8163 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-0.1482 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.1545 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +99 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -5.77500000e-01 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -4.17200000e-01 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -3.11100000e-01 2.82000000e-01 0.00000000e+00 +-1.80000000e+01 -2.07000000e-01 2.38000000e-01 0.00000000e+00 +-1.60000000e+01 -1.05100000e-01 1.96000000e-01 0.00000000e+00 +-1.40000000e+01 -8.50000000e-03 1.58000000e-01 0.00000000e+00 +-1.20000000e+01 7.67000000e-02 1.23000000e-01 0.00000000e+00 +-1.10000000e+01 1.12500000e-01 8.00000000e-02 0.00000000e+00 +-1.00000000e+01 1.42300000e-01 5.74000000e-02 0.00000000e+00 +-9.00000000e+00 1.58400000e-01 5.25000000e-02 0.00000000e+00 +-8.00000000e+00 1.50100000e-01 4.89000000e-02 0.00000000e+00 +-7.00000000e+00 1.18200000e-01 4.63000000e-02 0.00000000e+00 +-6.00000000e+00 8.39000000e-02 4.43000000e-02 0.00000000e+00 +-5.00000000e+00 5.77000000e-02 4.25000000e-02 0.00000000e+00 +-4.00000000e+00 3.68000000e-02 4.10000000e-02 0.00000000e+00 +-3.00000000e+00 2.33000000e-02 3.99000000e-02 0.00000000e+00 +-2.00000000e+00 1.54000000e-02 3.91000000e-02 0.00000000e+00 +-1.00000000e+00 4.50000000e-03 3.87000000e-02 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 3.85000000e-02 0.00000000e+00 + 1.00000000e+00 -4.50000000e-03 3.87000000e-02 0.00000000e+00 + 2.00000000e+00 -1.54000000e-02 3.91000000e-02 0.00000000e+00 + 3.00000000e+00 -2.33000000e-02 3.99000000e-02 0.00000000e+00 + 4.00000000e+00 -3.68000000e-02 4.10000000e-02 0.00000000e+00 + 5.00000000e+00 -5.77000000e-02 4.25000000e-02 0.00000000e+00 + 6.00000000e+00 -8.39000000e-02 4.43000000e-02 0.00000000e+00 + 7.00000000e+00 -1.18200000e-01 4.63000000e-02 0.00000000e+00 + 8.00000000e+00 -1.50100000e-01 4.89000000e-02 0.00000000e+00 + 9.00000000e+00 -1.58400000e-01 5.25000000e-02 0.00000000e+00 + 1.00000000e+01 -1.42300000e-01 5.74000000e-02 0.00000000e+00 + 1.10000000e+01 -1.12500000e-01 8.00000000e-02 0.00000000e+00 + 1.20000000e+01 -7.67000000e-02 1.23000000e-01 0.00000000e+00 + 1.40000000e+01 8.50000000e-03 1.58000000e-01 0.00000000e+00 + 1.60000000e+01 1.05100000e-01 1.96000000e-01 0.00000000e+00 + 1.80000000e+01 2.07000000e-01 2.38000000e-01 0.00000000e+00 + 2.00000000e+01 3.11100000e-01 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 4.17200000e-01 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 5.77500000e-01 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +! ------------------------------------------------------------------------------ +! data for table 2 +! ------------------------------------------------------------------------------ +0.02 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +9.154276388714532 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-9.154276388714532 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.1809 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-0.1809 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0286 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +97 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -5.79800000e-01 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -4.19800000e-01 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -3.15100000e-01 2.82000000e-01 0.00000000e+00 +-1.80000000e+01 -2.12000000e-01 2.38000000e-01 0.00000000e+00 +-1.60000000e+01 -1.11400000e-01 1.96000000e-01 0.00000000e+00 +-1.40000000e+01 -1.72000000e-02 1.58000000e-01 0.00000000e+00 +-1.20000000e+01 6.02000000e-02 1.23000000e-01 0.00000000e+00 +-1.00000000e+01 1.00300000e-01 6.30000000e-02 0.00000000e+00 +-9.00000000e+00 6.82000000e-02 3.96000000e-02 0.00000000e+00 +-8.00000000e+00 -2.14000000e-02 3.76000000e-02 0.00000000e+00 +-7.00000000e+00 -1.16100000e-01 3.58000000e-02 0.00000000e+00 +-6.00000000e+00 -1.58200000e-01 3.39000000e-02 0.00000000e+00 +-5.00000000e+00 -1.78800000e-01 3.23000000e-02 0.00000000e+00 +-4.00000000e+00 -1.78800000e-01 3.10000000e-02 0.00000000e+00 +-3.00000000e+00 -1.55000000e-01 2.99000000e-02 0.00000000e+00 +-2.00000000e+00 -1.13500000e-01 2.92000000e-02 0.00000000e+00 +-1.00000000e+00 -6.07000000e-02 2.88000000e-02 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 2.86000000e-02 0.00000000e+00 + 1.00000000e+00 6.07000000e-02 2.88000000e-02 0.00000000e+00 + 2.00000000e+00 1.13500000e-01 2.92000000e-02 0.00000000e+00 + 3.00000000e+00 1.55000000e-01 2.99000000e-02 0.00000000e+00 + 4.00000000e+00 1.78800000e-01 3.10000000e-02 0.00000000e+00 + 5.00000000e+00 1.78800000e-01 3.23000000e-02 0.00000000e+00 + 6.00000000e+00 1.58200000e-01 3.39000000e-02 0.00000000e+00 + 7.00000000e+00 1.16100000e-01 3.58000000e-02 0.00000000e+00 + 8.00000000e+00 2.14000000e-02 3.76000000e-02 0.00000000e+00 + 9.00000000e+00 -6.82000000e-02 3.96000000e-02 0.00000000e+00 + 1.00000000e+01 -1.00300000e-01 6.30000000e-02 0.00000000e+00 + 1.20000000e+01 -6.02000000e-02 1.23000000e-01 0.00000000e+00 + 1.40000000e+01 1.72000000e-02 1.58000000e-01 0.00000000e+00 + 1.60000000e+01 1.11400000e-01 1.96000000e-01 0.00000000e+00 + 1.80000000e+01 2.12000000e-01 2.38000000e-01 0.00000000e+00 + 2.00000000e+01 3.15100000e-01 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 4.19800000e-01 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 5.79800000e-01 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +! ------------------------------------------------------------------------------ +! data for table 3 +! ------------------------------------------------------------------------------ +0.04 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +10.299096322309719 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-10.299096322309719 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.4757 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-0.4757 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0214 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +97 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -5.84000000e-01 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -4.26500000e-01 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -3.23600000e-01 2.82000000e-01 0.00000000e+00 +-1.80000000e+01 -2.22800000e-01 2.38000000e-01 0.00000000e+00 +-1.60000000e+01 -1.28700000e-01 1.96000000e-01 0.00000000e+00 +-1.40000000e+01 -4.89000000e-02 1.58000000e-01 0.00000000e+00 +-1.20000000e+01 -1.39000000e-02 1.23000000e-01 0.00000000e+00 +-1.00000000e+01 -2.10800000e-01 6.20000000e-02 0.00000000e+00 +-9.00000000e+00 -3.54400000e-01 3.27000000e-02 0.00000000e+00 +-8.00000000e+00 -4.42800000e-01 3.03000000e-02 0.00000000e+00 +-7.00000000e+00 -4.75800000e-01 2.82000000e-02 0.00000000e+00 +-6.00000000e+00 -4.57300000e-01 2.63000000e-02 0.00000000e+00 +-5.00000000e+00 -4.11700000e-01 2.47000000e-02 0.00000000e+00 +-4.00000000e+00 -3.49500000e-01 2.35000000e-02 0.00000000e+00 +-3.00000000e+00 -2.68800000e-01 2.25000000e-02 0.00000000e+00 +-2.00000000e+00 -1.83300000e-01 2.19000000e-02 0.00000000e+00 +-1.00000000e+00 -9.36000000e-02 2.15000000e-02 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 2.14000000e-02 0.00000000e+00 + 1.00000000e+00 9.36000000e-02 2.15000000e-02 0.00000000e+00 + 2.00000000e+00 1.83300000e-01 2.19000000e-02 0.00000000e+00 + 3.00000000e+00 2.68800000e-01 2.25000000e-02 0.00000000e+00 + 4.00000000e+00 3.49500000e-01 2.35000000e-02 0.00000000e+00 + 5.00000000e+00 4.11700000e-01 2.47000000e-02 0.00000000e+00 + 6.00000000e+00 4.57300000e-01 2.63000000e-02 0.00000000e+00 + 7.00000000e+00 4.75800000e-01 2.82000000e-02 0.00000000e+00 + 8.00000000e+00 4.42800000e-01 3.03000000e-02 0.00000000e+00 + 9.00000000e+00 3.54400000e-01 3.27000000e-02 0.00000000e+00 + 1.00000000e+01 2.10800000e-01 6.20000000e-02 0.00000000e+00 + 1.20000000e+01 1.39000000e-02 1.23000000e-01 0.00000000e+00 + 1.40000000e+01 4.89000000e-02 1.58000000e-01 0.00000000e+00 + 1.60000000e+01 1.28700000e-01 1.96000000e-01 0.00000000e+00 + 1.80000000e+01 2.22800000e-01 2.38000000e-01 0.00000000e+00 + 2.00000000e+01 3.23600000e-01 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 4.26500000e-01 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 5.84000000e-01 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +! ------------------------------------------------------------------------------ +! data for table 4 +! ------------------------------------------------------------------------------ +0.08 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +11.587085702041861 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-11.587085702041861 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.6566 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-0.6566 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0162 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +99 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -5.96300000e-01 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -4.43000000e-01 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -3.47200000e-01 2.82000000e-01 0.00000000e+00 +-1.80000000e+01 -2.60300000e-01 2.38000000e-01 0.00000000e+00 +-1.60000000e+01 -2.02700000e-01 1.96000000e-01 0.00000000e+00 +-1.40000000e+01 -2.25600000e-01 1.58000000e-01 0.00000000e+00 +-1.20000000e+01 -4.40800000e-01 8.00000000e-02 0.00000000e+00 +-1.10000000e+01 -5.53100000e-01 3.15000000e-02 0.00000000e+00 +-1.00000000e+01 -6.24800000e-01 2.88000000e-02 0.00000000e+00 +-9.00000000e+00 -6.60600000e-01 2.64000000e-02 0.00000000e+00 +-8.00000000e+00 -6.58900000e-01 2.42000000e-02 0.00000000e+00 +-7.00000000e+00 -6.22400000e-01 2.23000000e-02 0.00000000e+00 +-6.00000000e+00 -5.61500000e-01 2.06000000e-02 0.00000000e+00 +-5.00000000e+00 -4.75300000e-01 1.92000000e-02 0.00000000e+00 +-4.00000000e+00 -3.88000000e-01 1.81000000e-02 0.00000000e+00 +-3.00000000e+00 -2.92400000e-01 1.72000000e-02 0.00000000e+00 +-2.00000000e+00 -1.93500000e-01 1.67000000e-02 0.00000000e+00 +-1.00000000e+00 -8.89000000e-02 1.63000000e-02 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 1.62000000e-02 0.00000000e+00 + 1.00000000e+00 8.89000000e-02 1.63000000e-02 0.00000000e+00 + 2.00000000e+00 1.93500000e-01 1.67000000e-02 0.00000000e+00 + 3.00000000e+00 2.92400000e-01 1.72000000e-02 0.00000000e+00 + 4.00000000e+00 3.88000000e-01 1.81000000e-02 0.00000000e+00 + 5.00000000e+00 4.75300000e-01 1.92000000e-02 0.00000000e+00 + 6.00000000e+00 5.61500000e-01 2.06000000e-02 0.00000000e+00 + 7.00000000e+00 6.22400000e-01 2.23000000e-02 0.00000000e+00 + 8.00000000e+00 6.58900000e-01 2.42000000e-02 0.00000000e+00 + 9.00000000e+00 6.60600000e-01 2.64000000e-02 0.00000000e+00 + 1.00000000e+01 6.24800000e-01 2.88000000e-02 0.00000000e+00 + 1.10000000e+01 5.53100000e-01 3.15000000e-02 0.00000000e+00 + 1.20000000e+01 4.40800000e-01 8.00000000e-02 0.00000000e+00 + 1.40000000e+01 2.25600000e-01 1.58000000e-01 0.00000000e+00 + 1.60000000e+01 2.02700000e-01 1.96000000e-01 0.00000000e+00 + 1.80000000e+01 2.60300000e-01 2.38000000e-01 0.00000000e+00 + 2.00000000e+01 3.47200000e-01 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 4.43000000e-01 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 5.96300000e-01 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +! ------------------------------------------------------------------------------ +! data for table 5 +! ------------------------------------------------------------------------------ +0.16 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +13.036149081898586 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-13.036149081898586 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.787 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-0.787 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0128 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +101 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -6.32100000e-01 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -5.02600000e-01 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -4.38200000e-01 2.82000000e-01 0.00000000e+00 +-1.80000000e+01 -4.20200000e-01 2.38000000e-01 0.00000000e+00 +-1.60000000e+01 -4.89600000e-01 1.96000000e-01 0.00000000e+00 +-1.40000000e+01 -6.23700000e-01 1.58000000e-01 0.00000000e+00 +-1.30000000e+01 -6.92300000e-01 7.70000000e-02 0.00000000e+00 +-1.20000000e+01 -7.48800000e-01 2.88000000e-02 0.00000000e+00 +-1.10000000e+01 -7.85200000e-01 2.62000000e-02 0.00000000e+00 +-1.00000000e+01 -7.94900000e-01 2.38000000e-02 0.00000000e+00 +-9.00000000e+00 -7.78100000e-01 2.17000000e-02 0.00000000e+00 +-8.00000000e+00 -7.37300000e-01 1.98000000e-02 0.00000000e+00 +-7.00000000e+00 -6.72400000e-01 1.81000000e-02 0.00000000e+00 +-6.00000000e+00 -5.96000000e-01 1.66000000e-02 0.00000000e+00 +-5.00000000e+00 -5.06800000e-01 1.53000000e-02 0.00000000e+00 +-4.00000000e+00 -4.11400000e-01 1.44000000e-02 0.00000000e+00 +-3.00000000e+00 -3.08800000e-01 1.37000000e-02 0.00000000e+00 +-2.00000000e+00 -2.20000000e-01 1.31000000e-02 0.00000000e+00 +-1.00000000e+00 -1.10000000e-01 1.29000000e-02 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 1.28000000e-02 0.00000000e+00 + 1.00000000e+00 1.10000000e-01 1.29000000e-02 0.00000000e+00 + 2.00000000e+00 2.20000000e-01 1.31000000e-02 0.00000000e+00 + 3.00000000e+00 3.08800000e-01 1.37000000e-02 0.00000000e+00 + 4.00000000e+00 4.11400000e-01 1.44000000e-02 0.00000000e+00 + 5.00000000e+00 5.06800000e-01 1.53000000e-02 0.00000000e+00 + 6.00000000e+00 5.96000000e-01 1.66000000e-02 0.00000000e+00 + 7.00000000e+00 6.72400000e-01 1.81000000e-02 0.00000000e+00 + 8.00000000e+00 7.37300000e-01 1.98000000e-02 0.00000000e+00 + 9.00000000e+00 7.78100000e-01 2.17000000e-02 0.00000000e+00 + 1.00000000e+01 7.94900000e-01 2.38000000e-02 0.00000000e+00 + 1.10000000e+01 7.85200000e-01 2.62000000e-02 0.00000000e+00 + 1.20000000e+01 7.48800000e-01 2.88000000e-02 0.00000000e+00 + 1.30000000e+01 6.92300000e-01 7.70000000e-02 0.00000000e+00 + 1.40000000e+01 6.23700000e-01 1.58000000e-01 0.00000000e+00 + 1.60000000e+01 4.89600000e-01 1.96000000e-01 0.00000000e+00 + 1.80000000e+01 4.20200000e-01 2.38000000e-01 0.00000000e+00 + 2.00000000e+01 4.38200000e-01 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 5.02600000e-01 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 6.32100000e-01 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +! ------------------------------------------------------------------------------ +! data for table 6 +! ------------------------------------------------------------------------------ +0.36 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +14.963057557300898 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-14.963057557300898 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.9125 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-0.9125 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0101 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +101 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -7.72400000e-01 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -7.05000000e-01 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -6.99700000e-01 2.82000000e-01 0.00000000e+00 +-1.80000000e+01 -7.31900000e-01 2.38000000e-01 0.00000000e+00 +-1.60000000e+01 -8.00700000e-01 1.96000000e-01 0.00000000e+00 +-1.40000000e+01 -8.80300000e-01 9.40000000e-02 0.00000000e+00 +-1.30000000e+01 -9.10400000e-01 2.59000000e-02 0.00000000e+00 +-1.20000000e+01 -9.27900000e-01 2.35000000e-02 0.00000000e+00 +-1.10000000e+01 -9.24900000e-01 2.13000000e-02 0.00000000e+00 +-1.00000000e+01 -8.98300000e-01 1.94000000e-02 0.00000000e+00 +-9.00000000e+00 -8.52600000e-01 1.76000000e-02 0.00000000e+00 +-8.00000000e+00 -7.87900000e-01 1.59000000e-02 0.00000000e+00 +-7.00000000e+00 -7.10000000e-01 1.45000000e-02 0.00000000e+00 +-6.00000000e+00 -6.22800000e-01 1.32000000e-02 0.00000000e+00 +-5.00000000e+00 -5.24000000e-01 1.21000000e-02 0.00000000e+00 +-4.00000000e+00 -4.40000000e-01 1.12000000e-02 0.00000000e+00 +-3.00000000e+00 -3.30000000e-01 1.07000000e-02 0.00000000e+00 +-2.00000000e+00 -2.20000000e-01 1.04000000e-02 0.00000000e+00 +-1.00000000e+00 -1.10000000e-01 1.02000000e-02 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 1.01000000e-02 0.00000000e+00 + 1.00000000e+00 1.10000000e-01 1.02000000e-02 0.00000000e+00 + 2.00000000e+00 2.20000000e-01 1.04000000e-02 0.00000000e+00 + 3.00000000e+00 3.30000000e-01 1.07000000e-02 0.00000000e+00 + 4.00000000e+00 4.40000000e-01 1.12000000e-02 0.00000000e+00 + 5.00000000e+00 5.24000000e-01 1.21000000e-02 0.00000000e+00 + 6.00000000e+00 6.22800000e-01 1.32000000e-02 0.00000000e+00 + 7.00000000e+00 7.10000000e-01 1.45000000e-02 0.00000000e+00 + 8.00000000e+00 7.87900000e-01 1.59000000e-02 0.00000000e+00 + 9.00000000e+00 8.52600000e-01 1.76000000e-02 0.00000000e+00 + 1.00000000e+01 8.98300000e-01 1.94000000e-02 0.00000000e+00 + 1.10000000e+01 9.24900000e-01 2.13000000e-02 0.00000000e+00 + 1.20000000e+01 9.27900000e-01 2.35000000e-02 0.00000000e+00 + 1.30000000e+01 9.10400000e-01 2.59000000e-02 0.00000000e+00 + 1.40000000e+01 8.80300000e-01 9.40000000e-02 0.00000000e+00 + 1.60000000e+01 8.00700000e-01 1.96000000e-01 0.00000000e+00 + 1.80000000e+01 7.31900000e-01 2.38000000e-01 0.00000000e+00 + 2.00000000e+01 6.99700000e-01 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 7.05000000e-01 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 7.72400000e-01 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +! ------------------------------------------------------------------------------ +! data for table 7 +! ------------------------------------------------------------------------------ +0.7 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +16.7538872411828 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-16.7538872411828 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.0075 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.0075 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0085 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +103 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -9.32600000e-01 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -8.86700000e-01 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -8.87700000e-01 2.82000000e-01 0.00000000e+00 +-1.80000000e+01 -9.15000000e-01 2.38000000e-01 0.00000000e+00 +-1.60000000e+01 -9.64800000e-01 1.96000000e-01 0.00000000e+00 +-1.50000000e+01 -9.93800000e-01 1.02000000e-01 0.00000000e+00 +-1.40000000e+01 -1.01750000e+00 2.45000000e-02 0.00000000e+00 +-1.30000000e+01 -1.02890000e+00 2.23000000e-02 0.00000000e+00 +-1.20000000e+01 -1.02450000e+00 2.02000000e-02 0.00000000e+00 +-1.10000000e+01 -9.97300000e-01 1.83000000e-02 0.00000000e+00 +-1.00000000e+01 -9.54100000e-01 1.66000000e-02 0.00000000e+00 +-9.00000000e+00 -8.90400000e-01 1.50000000e-02 0.00000000e+00 +-8.00000000e+00 -8.15600000e-01 1.36000000e-02 0.00000000e+00 +-7.00000000e+00 -7.29100000e-01 1.23000000e-02 0.00000000e+00 +-6.00000000e+00 -6.32800000e-01 1.12000000e-02 0.00000000e+00 +-5.00000000e+00 -5.50000000e-01 1.02000000e-02 0.00000000e+00 +-4.00000000e+00 -4.40000000e-01 9.60000000e-03 0.00000000e+00 +-3.00000000e+00 -3.30000000e-01 9.10000000e-03 0.00000000e+00 +-2.00000000e+00 -2.20000000e-01 8.80000000e-03 0.00000000e+00 +-1.00000000e+00 -1.10000000e-01 8.70000000e-03 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 8.50000000e-03 0.00000000e+00 + 1.00000000e+00 1.10000000e-01 8.70000000e-03 0.00000000e+00 + 2.00000000e+00 2.20000000e-01 8.80000000e-03 0.00000000e+00 + 3.00000000e+00 3.30000000e-01 9.10000000e-03 0.00000000e+00 + 4.00000000e+00 4.40000000e-01 9.60000000e-03 0.00000000e+00 + 5.00000000e+00 5.50000000e-01 1.02000000e-02 0.00000000e+00 + 6.00000000e+00 6.32800000e-01 1.12000000e-02 0.00000000e+00 + 7.00000000e+00 7.29100000e-01 1.23000000e-02 0.00000000e+00 + 8.00000000e+00 8.15600000e-01 1.36000000e-02 0.00000000e+00 + 9.00000000e+00 8.90400000e-01 1.50000000e-02 0.00000000e+00 + 1.00000000e+01 9.54100000e-01 1.66000000e-02 0.00000000e+00 + 1.10000000e+01 9.97300000e-01 1.83000000e-02 0.00000000e+00 + 1.20000000e+01 1.02450000e+00 2.02000000e-02 0.00000000e+00 + 1.30000000e+01 1.02890000e+00 2.23000000e-02 0.00000000e+00 + 1.40000000e+01 1.01750000e+00 2.45000000e-02 0.00000000e+00 + 1.50000000e+01 9.93800000e-01 1.02000000e-01 0.00000000e+00 + 1.60000000e+01 9.64800000e-01 1.96000000e-01 0.00000000e+00 + 1.80000000e+01 9.15000000e-01 2.38000000e-01 0.00000000e+00 + 2.00000000e+01 8.87700000e-01 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 8.86700000e-01 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 9.32600000e-01 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +! ------------------------------------------------------------------------------ +! data for table 8 +! ------------------------------------------------------------------------------ +1.0 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +17.801185316865297 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-17.801185316865297 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.0573 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.0573 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0082 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +103 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -1.01070000e+00 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -9.69600000e-01 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -9.70700000e-01 2.82000000e-01 0.00000000e+00 +-1.80000000e+01 -9.95900000e-01 2.38000000e-01 0.00000000e+00 +-1.60000000e+01 -1.04020000e+00 1.08000000e-01 0.00000000e+00 +-1.50000000e+01 -1.06240000e+00 2.51000000e-02 0.00000000e+00 +-1.40000000e+01 -1.07930000e+00 2.27000000e-02 0.00000000e+00 +-1.30000000e+01 -1.08040000e+00 2.06000000e-02 0.00000000e+00 +-1.20000000e+01 -1.06640000e+00 1.87000000e-02 0.00000000e+00 +-1.10000000e+01 -1.02840000e+00 1.70000000e-02 0.00000000e+00 +-1.00000000e+01 -9.75100000e-01 1.54000000e-02 0.00000000e+00 +-9.00000000e+00 -9.06700000e-01 1.39000000e-02 0.00000000e+00 +-8.00000000e+00 -8.25600000e-01 1.26000000e-02 0.00000000e+00 +-7.00000000e+00 -7.36200000e-01 1.15000000e-02 0.00000000e+00 +-6.00000000e+00 -6.60000000e-01 1.02000000e-02 0.00000000e+00 +-5.00000000e+00 -5.50000000e-01 9.50000000e-03 0.00000000e+00 +-4.00000000e+00 -4.40000000e-01 8.90000000e-03 0.00000000e+00 +-3.00000000e+00 -3.30000000e-01 8.60000000e-03 0.00000000e+00 +-2.00000000e+00 -2.20000000e-01 8.30000000e-03 0.00000000e+00 +-1.00000000e+00 -1.10000000e-01 8.20000000e-03 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 8.20000000e-03 0.00000000e+00 + 1.00000000e+00 1.10000000e-01 8.20000000e-03 0.00000000e+00 + 2.00000000e+00 2.20000000e-01 8.30000000e-03 0.00000000e+00 + 3.00000000e+00 3.30000000e-01 8.60000000e-03 0.00000000e+00 + 4.00000000e+00 4.40000000e-01 8.90000000e-03 0.00000000e+00 + 5.00000000e+00 5.50000000e-01 9.50000000e-03 0.00000000e+00 + 6.00000000e+00 6.60000000e-01 1.02000000e-02 0.00000000e+00 + 7.00000000e+00 7.36200000e-01 1.15000000e-02 0.00000000e+00 + 8.00000000e+00 8.25600000e-01 1.26000000e-02 0.00000000e+00 + 9.00000000e+00 9.06700000e-01 1.39000000e-02 0.00000000e+00 + 1.00000000e+01 9.75100000e-01 1.54000000e-02 0.00000000e+00 + 1.10000000e+01 1.02840000e+00 1.70000000e-02 0.00000000e+00 + 1.20000000e+01 1.06640000e+00 1.87000000e-02 0.00000000e+00 + 1.30000000e+01 1.08040000e+00 2.06000000e-02 0.00000000e+00 + 1.40000000e+01 1.07930000e+00 2.27000000e-02 0.00000000e+00 + 1.50000000e+01 1.06240000e+00 2.51000000e-02 0.00000000e+00 + 1.60000000e+01 1.04020000e+00 1.08000000e-01 0.00000000e+00 + 1.80000000e+01 9.95900000e-01 2.38000000e-01 0.00000000e+00 + 2.00000000e+01 9.70700000e-01 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 9.69600000e-01 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 1.01070000e+00 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +! ------------------------------------------------------------------------------ +! data for table 9 +! ------------------------------------------------------------------------------ +2.0 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +20.027374578257152 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-20.027374578257152 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.151 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.151 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0077 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +105 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -1.14680000e+00 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -1.11270000e+00 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -1.11720000e+00 2.82000000e-01 0.00000000e+00 +-1.80000000e+01 -1.13830000e+00 2.38000000e-01 0.00000000e+00 +-1.70000000e+01 -1.15500000e+00 1.20000000e-01 0.00000000e+00 +-1.60000000e+01 -1.16950000e+00 2.40000000e-02 0.00000000e+00 +-1.50000000e+01 -1.18130000e+00 2.18000000e-02 0.00000000e+00 +-1.40000000e+01 -1.18130000e+00 1.97000000e-02 0.00000000e+00 +-1.30000000e+01 -1.16620000e+00 1.79000000e-02 0.00000000e+00 +-1.20000000e+01 -1.12960000e+00 1.63000000e-02 0.00000000e+00 +-1.10000000e+01 -1.07720000e+00 1.48000000e-02 0.00000000e+00 +-1.00000000e+01 -1.01110000e+00 1.34000000e-02 0.00000000e+00 +-9.00000000e+00 -9.31400000e-01 1.22000000e-02 0.00000000e+00 +-8.00000000e+00 -8.43900000e-01 1.11000000e-02 0.00000000e+00 +-7.00000000e+00 -7.44900000e-01 1.01000000e-02 0.00000000e+00 +-6.00000000e+00 -6.60000000e-01 9.30000000e-03 0.00000000e+00 +-5.00000000e+00 -5.50000000e-01 8.70000000e-03 0.00000000e+00 +-4.00000000e+00 -4.40000000e-01 8.40000000e-03 0.00000000e+00 +-3.00000000e+00 -3.30000000e-01 8.00000000e-03 0.00000000e+00 +-2.00000000e+00 -2.20000000e-01 7.80000000e-03 0.00000000e+00 +-1.00000000e+00 -1.10000000e-01 7.70000000e-03 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 7.70000000e-03 0.00000000e+00 + 1.00000000e+00 1.10000000e-01 7.70000000e-03 0.00000000e+00 + 2.00000000e+00 2.20000000e-01 7.80000000e-03 0.00000000e+00 + 3.00000000e+00 3.30000000e-01 8.00000000e-03 0.00000000e+00 + 4.00000000e+00 4.40000000e-01 8.40000000e-03 0.00000000e+00 + 5.00000000e+00 5.50000000e-01 8.70000000e-03 0.00000000e+00 + 6.00000000e+00 6.60000000e-01 9.30000000e-03 0.00000000e+00 + 7.00000000e+00 7.44900000e-01 1.01000000e-02 0.00000000e+00 + 8.00000000e+00 8.43900000e-01 1.11000000e-02 0.00000000e+00 + 9.00000000e+00 9.31400000e-01 1.22000000e-02 0.00000000e+00 + 1.00000000e+01 1.01110000e+00 1.34000000e-02 0.00000000e+00 + 1.10000000e+01 1.07720000e+00 1.48000000e-02 0.00000000e+00 + 1.20000000e+01 1.12960000e+00 1.63000000e-02 0.00000000e+00 + 1.30000000e+01 1.16620000e+00 1.79000000e-02 0.00000000e+00 + 1.40000000e+01 1.18130000e+00 1.97000000e-02 0.00000000e+00 + 1.50000000e+01 1.18130000e+00 2.18000000e-02 0.00000000e+00 + 1.60000000e+01 1.16950000e+00 2.40000000e-02 0.00000000e+00 + 1.70000000e+01 1.15500000e+00 1.20000000e-01 0.00000000e+00 + 1.80000000e+01 1.13830000e+00 2.38000000e-01 0.00000000e+00 + 2.00000000e+01 1.11720000e+00 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 1.11270000e+00 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 1.14680000e+00 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +! ------------------------------------------------------------------------------ +! data for table 10 +! ------------------------------------------------------------------------------ +5.0 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +23.403123375221707 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-23.403123375221707 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.2617 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.2617 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0073 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +107 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -1.29250000e+00 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -1.27140000e+00 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -1.27680000e+00 2.82000000e-01 0.00000000e+00 +-1.90000000e+01 -1.28530000e+00 1.40000000e-01 0.00000000e+00 +-1.80000000e+01 -1.29600000e+00 2.44000000e-02 0.00000000e+00 +-1.70000000e+01 -1.30380000e+00 2.23000000e-02 0.00000000e+00 +-1.60000000e+01 -1.30670000e+00 2.03000000e-02 0.00000000e+00 +-1.50000000e+01 -1.30040000e+00 1.85000000e-02 0.00000000e+00 +-1.40000000e+01 -1.28080000e+00 1.68000000e-02 0.00000000e+00 +-1.30000000e+01 -1.24300000e+00 1.53000000e-02 0.00000000e+00 +-1.20000000e+01 -1.18840000e+00 1.40000000e-02 0.00000000e+00 +-1.10000000e+01 -1.12110000e+00 1.28000000e-02 0.00000000e+00 +-1.00000000e+01 -1.04040000e+00 1.17000000e-02 0.00000000e+00 +-9.00000000e+00 -9.52500000e-01 1.08000000e-02 0.00000000e+00 +-8.00000000e+00 -8.53800000e-01 1.00000000e-02 0.00000000e+00 +-7.00000000e+00 -7.70000000e-01 9.30000000e-03 0.00000000e+00 +-6.00000000e+00 -6.60000000e-01 8.70000000e-03 0.00000000e+00 +-5.00000000e+00 -5.50000000e-01 8.30000000e-03 0.00000000e+00 +-4.00000000e+00 -4.40000000e-01 7.90000000e-03 0.00000000e+00 +-3.00000000e+00 -3.30000000e-01 7.70000000e-03 0.00000000e+00 +-2.00000000e+00 -2.20000000e-01 7.50000000e-03 0.00000000e+00 +-1.00000000e+00 -1.10000000e-01 7.30000000e-03 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 7.30000000e-03 0.00000000e+00 + 1.00000000e+00 1.10000000e-01 7.30000000e-03 0.00000000e+00 + 2.00000000e+00 2.20000000e-01 7.50000000e-03 0.00000000e+00 + 3.00000000e+00 3.30000000e-01 7.70000000e-03 0.00000000e+00 + 4.00000000e+00 4.40000000e-01 7.90000000e-03 0.00000000e+00 + 5.00000000e+00 5.50000000e-01 8.30000000e-03 0.00000000e+00 + 6.00000000e+00 6.60000000e-01 8.70000000e-03 0.00000000e+00 + 7.00000000e+00 7.70000000e-01 9.30000000e-03 0.00000000e+00 + 8.00000000e+00 8.53800000e-01 1.00000000e-02 0.00000000e+00 + 9.00000000e+00 9.52500000e-01 1.08000000e-02 0.00000000e+00 + 1.00000000e+01 1.04040000e+00 1.17000000e-02 0.00000000e+00 + 1.10000000e+01 1.12110000e+00 1.28000000e-02 0.00000000e+00 + 1.20000000e+01 1.18840000e+00 1.40000000e-02 0.00000000e+00 + 1.30000000e+01 1.24300000e+00 1.53000000e-02 0.00000000e+00 + 1.40000000e+01 1.28080000e+00 1.68000000e-02 0.00000000e+00 + 1.50000000e+01 1.30040000e+00 1.85000000e-02 0.00000000e+00 + 1.60000000e+01 1.30670000e+00 2.03000000e-02 0.00000000e+00 + 1.70000000e+01 1.30380000e+00 2.23000000e-02 0.00000000e+00 + 1.80000000e+01 1.29600000e+00 2.44000000e-02 0.00000000e+00 + 1.90000000e+01 1.28530000e+00 1.40000000e-01 0.00000000e+00 + 2.00000000e+01 1.27680000e+00 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 1.27140000e+00 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 1.29250000e+00 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 + diff --git a/examples/helical_riverine/airfoils/NACA_0021.dat b/examples/helical_riverine/airfoils/NACA_0021.dat index 086fb2f0..e4b94c5a 100644 --- a/examples/helical_riverine/airfoils/NACA_0021.dat +++ b/examples/helical_riverine/airfoils/NACA_0021.dat @@ -1,1211 +1,1464 @@ -Title: NACA0021 -Thickness to Chord Ratio: 0.21 -Zero Lift AOA (deg): 0.0 -Reverse Camber Direction: 0 +! ------------ AirfoilInfo v1.01.x Input File ---------------------------------- +! NACA 0018 at Re = 0.01,0.02,0.04,0.08,0.16,0.36,0.70,1,2,5 million +! line +! line +! ------------------------------------------------------------------------------ +DEFAULT InterpOrd - ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] +0.18 RelThickness - ! The non-dimensional thickness of the airfoil (thickness/chord) [only used if UAMod=7] [default=0.2] (-) +1 NonDimArea - ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) +@"NACA_0018_Coords.txt" NumCoords - ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +"NA" BL_file - ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. +10 NumTabs - ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. +! ------------------------------------------------------------------------------ +! data for table 1 +! ------------------------------------------------------------------------------ +0.01 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +8.136711569484852 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-8.136711569484852 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.8163 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-0.1482 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.1545 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +99 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -5.77500000e-01 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -4.17200000e-01 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -3.11100000e-01 2.82000000e-01 0.00000000e+00 +-1.80000000e+01 -2.07000000e-01 2.38000000e-01 0.00000000e+00 +-1.60000000e+01 -1.05100000e-01 1.96000000e-01 0.00000000e+00 +-1.40000000e+01 -8.50000000e-03 1.58000000e-01 0.00000000e+00 +-1.20000000e+01 7.67000000e-02 1.23000000e-01 0.00000000e+00 +-1.10000000e+01 1.12500000e-01 8.00000000e-02 0.00000000e+00 +-1.00000000e+01 1.42300000e-01 5.74000000e-02 0.00000000e+00 +-9.00000000e+00 1.58400000e-01 5.25000000e-02 0.00000000e+00 +-8.00000000e+00 1.50100000e-01 4.89000000e-02 0.00000000e+00 +-7.00000000e+00 1.18200000e-01 4.63000000e-02 0.00000000e+00 +-6.00000000e+00 8.39000000e-02 4.43000000e-02 0.00000000e+00 +-5.00000000e+00 5.77000000e-02 4.25000000e-02 0.00000000e+00 +-4.00000000e+00 3.68000000e-02 4.10000000e-02 0.00000000e+00 +-3.00000000e+00 2.33000000e-02 3.99000000e-02 0.00000000e+00 +-2.00000000e+00 1.54000000e-02 3.91000000e-02 0.00000000e+00 +-1.00000000e+00 4.50000000e-03 3.87000000e-02 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 3.85000000e-02 0.00000000e+00 + 1.00000000e+00 -4.50000000e-03 3.87000000e-02 0.00000000e+00 + 2.00000000e+00 -1.54000000e-02 3.91000000e-02 0.00000000e+00 + 3.00000000e+00 -2.33000000e-02 3.99000000e-02 0.00000000e+00 + 4.00000000e+00 -3.68000000e-02 4.10000000e-02 0.00000000e+00 + 5.00000000e+00 -5.77000000e-02 4.25000000e-02 0.00000000e+00 + 6.00000000e+00 -8.39000000e-02 4.43000000e-02 0.00000000e+00 + 7.00000000e+00 -1.18200000e-01 4.63000000e-02 0.00000000e+00 + 8.00000000e+00 -1.50100000e-01 4.89000000e-02 0.00000000e+00 + 9.00000000e+00 -1.58400000e-01 5.25000000e-02 0.00000000e+00 + 1.00000000e+01 -1.42300000e-01 5.74000000e-02 0.00000000e+00 + 1.10000000e+01 -1.12500000e-01 8.00000000e-02 0.00000000e+00 + 1.20000000e+01 -7.67000000e-02 1.23000000e-01 0.00000000e+00 + 1.40000000e+01 8.50000000e-03 1.58000000e-01 0.00000000e+00 + 1.60000000e+01 1.05100000e-01 1.96000000e-01 0.00000000e+00 + 1.80000000e+01 2.07000000e-01 2.38000000e-01 0.00000000e+00 + 2.00000000e+01 3.11100000e-01 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 4.17200000e-01 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 5.77500000e-01 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +! ------------------------------------------------------------------------------ +! data for table 2 +! ------------------------------------------------------------------------------ +0.02 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +9.154276388714532 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-9.154276388714532 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.1809 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-0.1809 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0286 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +97 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -5.79800000e-01 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -4.19800000e-01 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -3.15100000e-01 2.82000000e-01 0.00000000e+00 +-1.80000000e+01 -2.12000000e-01 2.38000000e-01 0.00000000e+00 +-1.60000000e+01 -1.11400000e-01 1.96000000e-01 0.00000000e+00 +-1.40000000e+01 -1.72000000e-02 1.58000000e-01 0.00000000e+00 +-1.20000000e+01 6.02000000e-02 1.23000000e-01 0.00000000e+00 +-1.00000000e+01 1.00300000e-01 6.30000000e-02 0.00000000e+00 +-9.00000000e+00 6.82000000e-02 3.96000000e-02 0.00000000e+00 +-8.00000000e+00 -2.14000000e-02 3.76000000e-02 0.00000000e+00 +-7.00000000e+00 -1.16100000e-01 3.58000000e-02 0.00000000e+00 +-6.00000000e+00 -1.58200000e-01 3.39000000e-02 0.00000000e+00 +-5.00000000e+00 -1.78800000e-01 3.23000000e-02 0.00000000e+00 +-4.00000000e+00 -1.78800000e-01 3.10000000e-02 0.00000000e+00 +-3.00000000e+00 -1.55000000e-01 2.99000000e-02 0.00000000e+00 +-2.00000000e+00 -1.13500000e-01 2.92000000e-02 0.00000000e+00 +-1.00000000e+00 -6.07000000e-02 2.88000000e-02 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 2.86000000e-02 0.00000000e+00 + 1.00000000e+00 6.07000000e-02 2.88000000e-02 0.00000000e+00 + 2.00000000e+00 1.13500000e-01 2.92000000e-02 0.00000000e+00 + 3.00000000e+00 1.55000000e-01 2.99000000e-02 0.00000000e+00 + 4.00000000e+00 1.78800000e-01 3.10000000e-02 0.00000000e+00 + 5.00000000e+00 1.78800000e-01 3.23000000e-02 0.00000000e+00 + 6.00000000e+00 1.58200000e-01 3.39000000e-02 0.00000000e+00 + 7.00000000e+00 1.16100000e-01 3.58000000e-02 0.00000000e+00 + 8.00000000e+00 2.14000000e-02 3.76000000e-02 0.00000000e+00 + 9.00000000e+00 -6.82000000e-02 3.96000000e-02 0.00000000e+00 + 1.00000000e+01 -1.00300000e-01 6.30000000e-02 0.00000000e+00 + 1.20000000e+01 -6.02000000e-02 1.23000000e-01 0.00000000e+00 + 1.40000000e+01 1.72000000e-02 1.58000000e-01 0.00000000e+00 + 1.60000000e+01 1.11400000e-01 1.96000000e-01 0.00000000e+00 + 1.80000000e+01 2.12000000e-01 2.38000000e-01 0.00000000e+00 + 2.00000000e+01 3.15100000e-01 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 4.19800000e-01 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 5.79800000e-01 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +! ------------------------------------------------------------------------------ +! data for table 3 +! ------------------------------------------------------------------------------ +0.04 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +10.299096322309719 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-10.299096322309719 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.4757 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-0.4757 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0214 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +97 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -5.84000000e-01 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -4.26500000e-01 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -3.23600000e-01 2.82000000e-01 0.00000000e+00 +-1.80000000e+01 -2.22800000e-01 2.38000000e-01 0.00000000e+00 +-1.60000000e+01 -1.28700000e-01 1.96000000e-01 0.00000000e+00 +-1.40000000e+01 -4.89000000e-02 1.58000000e-01 0.00000000e+00 +-1.20000000e+01 -1.39000000e-02 1.23000000e-01 0.00000000e+00 +-1.00000000e+01 -2.10800000e-01 6.20000000e-02 0.00000000e+00 +-9.00000000e+00 -3.54400000e-01 3.27000000e-02 0.00000000e+00 +-8.00000000e+00 -4.42800000e-01 3.03000000e-02 0.00000000e+00 +-7.00000000e+00 -4.75800000e-01 2.82000000e-02 0.00000000e+00 +-6.00000000e+00 -4.57300000e-01 2.63000000e-02 0.00000000e+00 +-5.00000000e+00 -4.11700000e-01 2.47000000e-02 0.00000000e+00 +-4.00000000e+00 -3.49500000e-01 2.35000000e-02 0.00000000e+00 +-3.00000000e+00 -2.68800000e-01 2.25000000e-02 0.00000000e+00 +-2.00000000e+00 -1.83300000e-01 2.19000000e-02 0.00000000e+00 +-1.00000000e+00 -9.36000000e-02 2.15000000e-02 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 2.14000000e-02 0.00000000e+00 + 1.00000000e+00 9.36000000e-02 2.15000000e-02 0.00000000e+00 + 2.00000000e+00 1.83300000e-01 2.19000000e-02 0.00000000e+00 + 3.00000000e+00 2.68800000e-01 2.25000000e-02 0.00000000e+00 + 4.00000000e+00 3.49500000e-01 2.35000000e-02 0.00000000e+00 + 5.00000000e+00 4.11700000e-01 2.47000000e-02 0.00000000e+00 + 6.00000000e+00 4.57300000e-01 2.63000000e-02 0.00000000e+00 + 7.00000000e+00 4.75800000e-01 2.82000000e-02 0.00000000e+00 + 8.00000000e+00 4.42800000e-01 3.03000000e-02 0.00000000e+00 + 9.00000000e+00 3.54400000e-01 3.27000000e-02 0.00000000e+00 + 1.00000000e+01 2.10800000e-01 6.20000000e-02 0.00000000e+00 + 1.20000000e+01 1.39000000e-02 1.23000000e-01 0.00000000e+00 + 1.40000000e+01 4.89000000e-02 1.58000000e-01 0.00000000e+00 + 1.60000000e+01 1.28700000e-01 1.96000000e-01 0.00000000e+00 + 1.80000000e+01 2.22800000e-01 2.38000000e-01 0.00000000e+00 + 2.00000000e+01 3.23600000e-01 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 4.26500000e-01 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 5.84000000e-01 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +! ------------------------------------------------------------------------------ +! data for table 4 +! ------------------------------------------------------------------------------ +0.08 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +11.587085702041861 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-11.587085702041861 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.6566 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-0.6566 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0162 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +99 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -5.96300000e-01 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -4.43000000e-01 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -3.47200000e-01 2.82000000e-01 0.00000000e+00 +-1.80000000e+01 -2.60300000e-01 2.38000000e-01 0.00000000e+00 +-1.60000000e+01 -2.02700000e-01 1.96000000e-01 0.00000000e+00 +-1.40000000e+01 -2.25600000e-01 1.58000000e-01 0.00000000e+00 +-1.20000000e+01 -4.40800000e-01 8.00000000e-02 0.00000000e+00 +-1.10000000e+01 -5.53100000e-01 3.15000000e-02 0.00000000e+00 +-1.00000000e+01 -6.24800000e-01 2.88000000e-02 0.00000000e+00 +-9.00000000e+00 -6.60600000e-01 2.64000000e-02 0.00000000e+00 +-8.00000000e+00 -6.58900000e-01 2.42000000e-02 0.00000000e+00 +-7.00000000e+00 -6.22400000e-01 2.23000000e-02 0.00000000e+00 +-6.00000000e+00 -5.61500000e-01 2.06000000e-02 0.00000000e+00 +-5.00000000e+00 -4.75300000e-01 1.92000000e-02 0.00000000e+00 +-4.00000000e+00 -3.88000000e-01 1.81000000e-02 0.00000000e+00 +-3.00000000e+00 -2.92400000e-01 1.72000000e-02 0.00000000e+00 +-2.00000000e+00 -1.93500000e-01 1.67000000e-02 0.00000000e+00 +-1.00000000e+00 -8.89000000e-02 1.63000000e-02 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 1.62000000e-02 0.00000000e+00 + 1.00000000e+00 8.89000000e-02 1.63000000e-02 0.00000000e+00 + 2.00000000e+00 1.93500000e-01 1.67000000e-02 0.00000000e+00 + 3.00000000e+00 2.92400000e-01 1.72000000e-02 0.00000000e+00 + 4.00000000e+00 3.88000000e-01 1.81000000e-02 0.00000000e+00 + 5.00000000e+00 4.75300000e-01 1.92000000e-02 0.00000000e+00 + 6.00000000e+00 5.61500000e-01 2.06000000e-02 0.00000000e+00 + 7.00000000e+00 6.22400000e-01 2.23000000e-02 0.00000000e+00 + 8.00000000e+00 6.58900000e-01 2.42000000e-02 0.00000000e+00 + 9.00000000e+00 6.60600000e-01 2.64000000e-02 0.00000000e+00 + 1.00000000e+01 6.24800000e-01 2.88000000e-02 0.00000000e+00 + 1.10000000e+01 5.53100000e-01 3.15000000e-02 0.00000000e+00 + 1.20000000e+01 4.40800000e-01 8.00000000e-02 0.00000000e+00 + 1.40000000e+01 2.25600000e-01 1.58000000e-01 0.00000000e+00 + 1.60000000e+01 2.02700000e-01 1.96000000e-01 0.00000000e+00 + 1.80000000e+01 2.60300000e-01 2.38000000e-01 0.00000000e+00 + 2.00000000e+01 3.47200000e-01 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 4.43000000e-01 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 5.96300000e-01 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +! ------------------------------------------------------------------------------ +! data for table 5 +! ------------------------------------------------------------------------------ +0.16 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +13.036149081898586 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-13.036149081898586 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.787 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-0.787 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0128 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +101 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -6.32100000e-01 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -5.02600000e-01 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -4.38200000e-01 2.82000000e-01 0.00000000e+00 +-1.80000000e+01 -4.20200000e-01 2.38000000e-01 0.00000000e+00 +-1.60000000e+01 -4.89600000e-01 1.96000000e-01 0.00000000e+00 +-1.40000000e+01 -6.23700000e-01 1.58000000e-01 0.00000000e+00 +-1.30000000e+01 -6.92300000e-01 7.70000000e-02 0.00000000e+00 +-1.20000000e+01 -7.48800000e-01 2.88000000e-02 0.00000000e+00 +-1.10000000e+01 -7.85200000e-01 2.62000000e-02 0.00000000e+00 +-1.00000000e+01 -7.94900000e-01 2.38000000e-02 0.00000000e+00 +-9.00000000e+00 -7.78100000e-01 2.17000000e-02 0.00000000e+00 +-8.00000000e+00 -7.37300000e-01 1.98000000e-02 0.00000000e+00 +-7.00000000e+00 -6.72400000e-01 1.81000000e-02 0.00000000e+00 +-6.00000000e+00 -5.96000000e-01 1.66000000e-02 0.00000000e+00 +-5.00000000e+00 -5.06800000e-01 1.53000000e-02 0.00000000e+00 +-4.00000000e+00 -4.11400000e-01 1.44000000e-02 0.00000000e+00 +-3.00000000e+00 -3.08800000e-01 1.37000000e-02 0.00000000e+00 +-2.00000000e+00 -2.20000000e-01 1.31000000e-02 0.00000000e+00 +-1.00000000e+00 -1.10000000e-01 1.29000000e-02 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 1.28000000e-02 0.00000000e+00 + 1.00000000e+00 1.10000000e-01 1.29000000e-02 0.00000000e+00 + 2.00000000e+00 2.20000000e-01 1.31000000e-02 0.00000000e+00 + 3.00000000e+00 3.08800000e-01 1.37000000e-02 0.00000000e+00 + 4.00000000e+00 4.11400000e-01 1.44000000e-02 0.00000000e+00 + 5.00000000e+00 5.06800000e-01 1.53000000e-02 0.00000000e+00 + 6.00000000e+00 5.96000000e-01 1.66000000e-02 0.00000000e+00 + 7.00000000e+00 6.72400000e-01 1.81000000e-02 0.00000000e+00 + 8.00000000e+00 7.37300000e-01 1.98000000e-02 0.00000000e+00 + 9.00000000e+00 7.78100000e-01 2.17000000e-02 0.00000000e+00 + 1.00000000e+01 7.94900000e-01 2.38000000e-02 0.00000000e+00 + 1.10000000e+01 7.85200000e-01 2.62000000e-02 0.00000000e+00 + 1.20000000e+01 7.48800000e-01 2.88000000e-02 0.00000000e+00 + 1.30000000e+01 6.92300000e-01 7.70000000e-02 0.00000000e+00 + 1.40000000e+01 6.23700000e-01 1.58000000e-01 0.00000000e+00 + 1.60000000e+01 4.89600000e-01 1.96000000e-01 0.00000000e+00 + 1.80000000e+01 4.20200000e-01 2.38000000e-01 0.00000000e+00 + 2.00000000e+01 4.38200000e-01 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 5.02600000e-01 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 6.32100000e-01 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +! ------------------------------------------------------------------------------ +! data for table 6 +! ------------------------------------------------------------------------------ +0.36 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +14.963057557300898 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-14.963057557300898 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.9125 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-0.9125 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0101 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +101 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -7.72400000e-01 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -7.05000000e-01 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -6.99700000e-01 2.82000000e-01 0.00000000e+00 +-1.80000000e+01 -7.31900000e-01 2.38000000e-01 0.00000000e+00 +-1.60000000e+01 -8.00700000e-01 1.96000000e-01 0.00000000e+00 +-1.40000000e+01 -8.80300000e-01 9.40000000e-02 0.00000000e+00 +-1.30000000e+01 -9.10400000e-01 2.59000000e-02 0.00000000e+00 +-1.20000000e+01 -9.27900000e-01 2.35000000e-02 0.00000000e+00 +-1.10000000e+01 -9.24900000e-01 2.13000000e-02 0.00000000e+00 +-1.00000000e+01 -8.98300000e-01 1.94000000e-02 0.00000000e+00 +-9.00000000e+00 -8.52600000e-01 1.76000000e-02 0.00000000e+00 +-8.00000000e+00 -7.87900000e-01 1.59000000e-02 0.00000000e+00 +-7.00000000e+00 -7.10000000e-01 1.45000000e-02 0.00000000e+00 +-6.00000000e+00 -6.22800000e-01 1.32000000e-02 0.00000000e+00 +-5.00000000e+00 -5.24000000e-01 1.21000000e-02 0.00000000e+00 +-4.00000000e+00 -4.40000000e-01 1.12000000e-02 0.00000000e+00 +-3.00000000e+00 -3.30000000e-01 1.07000000e-02 0.00000000e+00 +-2.00000000e+00 -2.20000000e-01 1.04000000e-02 0.00000000e+00 +-1.00000000e+00 -1.10000000e-01 1.02000000e-02 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 1.01000000e-02 0.00000000e+00 + 1.00000000e+00 1.10000000e-01 1.02000000e-02 0.00000000e+00 + 2.00000000e+00 2.20000000e-01 1.04000000e-02 0.00000000e+00 + 3.00000000e+00 3.30000000e-01 1.07000000e-02 0.00000000e+00 + 4.00000000e+00 4.40000000e-01 1.12000000e-02 0.00000000e+00 + 5.00000000e+00 5.24000000e-01 1.21000000e-02 0.00000000e+00 + 6.00000000e+00 6.22800000e-01 1.32000000e-02 0.00000000e+00 + 7.00000000e+00 7.10000000e-01 1.45000000e-02 0.00000000e+00 + 8.00000000e+00 7.87900000e-01 1.59000000e-02 0.00000000e+00 + 9.00000000e+00 8.52600000e-01 1.76000000e-02 0.00000000e+00 + 1.00000000e+01 8.98300000e-01 1.94000000e-02 0.00000000e+00 + 1.10000000e+01 9.24900000e-01 2.13000000e-02 0.00000000e+00 + 1.20000000e+01 9.27900000e-01 2.35000000e-02 0.00000000e+00 + 1.30000000e+01 9.10400000e-01 2.59000000e-02 0.00000000e+00 + 1.40000000e+01 8.80300000e-01 9.40000000e-02 0.00000000e+00 + 1.60000000e+01 8.00700000e-01 1.96000000e-01 0.00000000e+00 + 1.80000000e+01 7.31900000e-01 2.38000000e-01 0.00000000e+00 + 2.00000000e+01 6.99700000e-01 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 7.05000000e-01 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 7.72400000e-01 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +! ------------------------------------------------------------------------------ +! data for table 7 +! ------------------------------------------------------------------------------ +0.7 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +16.7538872411828 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-16.7538872411828 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.0075 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.0075 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0085 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +103 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -9.32600000e-01 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -8.86700000e-01 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -8.87700000e-01 2.82000000e-01 0.00000000e+00 +-1.80000000e+01 -9.15000000e-01 2.38000000e-01 0.00000000e+00 +-1.60000000e+01 -9.64800000e-01 1.96000000e-01 0.00000000e+00 +-1.50000000e+01 -9.93800000e-01 1.02000000e-01 0.00000000e+00 +-1.40000000e+01 -1.01750000e+00 2.45000000e-02 0.00000000e+00 +-1.30000000e+01 -1.02890000e+00 2.23000000e-02 0.00000000e+00 +-1.20000000e+01 -1.02450000e+00 2.02000000e-02 0.00000000e+00 +-1.10000000e+01 -9.97300000e-01 1.83000000e-02 0.00000000e+00 +-1.00000000e+01 -9.54100000e-01 1.66000000e-02 0.00000000e+00 +-9.00000000e+00 -8.90400000e-01 1.50000000e-02 0.00000000e+00 +-8.00000000e+00 -8.15600000e-01 1.36000000e-02 0.00000000e+00 +-7.00000000e+00 -7.29100000e-01 1.23000000e-02 0.00000000e+00 +-6.00000000e+00 -6.32800000e-01 1.12000000e-02 0.00000000e+00 +-5.00000000e+00 -5.50000000e-01 1.02000000e-02 0.00000000e+00 +-4.00000000e+00 -4.40000000e-01 9.60000000e-03 0.00000000e+00 +-3.00000000e+00 -3.30000000e-01 9.10000000e-03 0.00000000e+00 +-2.00000000e+00 -2.20000000e-01 8.80000000e-03 0.00000000e+00 +-1.00000000e+00 -1.10000000e-01 8.70000000e-03 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 8.50000000e-03 0.00000000e+00 + 1.00000000e+00 1.10000000e-01 8.70000000e-03 0.00000000e+00 + 2.00000000e+00 2.20000000e-01 8.80000000e-03 0.00000000e+00 + 3.00000000e+00 3.30000000e-01 9.10000000e-03 0.00000000e+00 + 4.00000000e+00 4.40000000e-01 9.60000000e-03 0.00000000e+00 + 5.00000000e+00 5.50000000e-01 1.02000000e-02 0.00000000e+00 + 6.00000000e+00 6.32800000e-01 1.12000000e-02 0.00000000e+00 + 7.00000000e+00 7.29100000e-01 1.23000000e-02 0.00000000e+00 + 8.00000000e+00 8.15600000e-01 1.36000000e-02 0.00000000e+00 + 9.00000000e+00 8.90400000e-01 1.50000000e-02 0.00000000e+00 + 1.00000000e+01 9.54100000e-01 1.66000000e-02 0.00000000e+00 + 1.10000000e+01 9.97300000e-01 1.83000000e-02 0.00000000e+00 + 1.20000000e+01 1.02450000e+00 2.02000000e-02 0.00000000e+00 + 1.30000000e+01 1.02890000e+00 2.23000000e-02 0.00000000e+00 + 1.40000000e+01 1.01750000e+00 2.45000000e-02 0.00000000e+00 + 1.50000000e+01 9.93800000e-01 1.02000000e-01 0.00000000e+00 + 1.60000000e+01 9.64800000e-01 1.96000000e-01 0.00000000e+00 + 1.80000000e+01 9.15000000e-01 2.38000000e-01 0.00000000e+00 + 2.00000000e+01 8.87700000e-01 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 8.86700000e-01 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 9.32600000e-01 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +! ------------------------------------------------------------------------------ +! data for table 8 +! ------------------------------------------------------------------------------ +1.0 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +17.801185316865297 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-17.801185316865297 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.0573 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.0573 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0082 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +103 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -1.01070000e+00 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -9.69600000e-01 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -9.70700000e-01 2.82000000e-01 0.00000000e+00 +-1.80000000e+01 -9.95900000e-01 2.38000000e-01 0.00000000e+00 +-1.60000000e+01 -1.04020000e+00 1.08000000e-01 0.00000000e+00 +-1.50000000e+01 -1.06240000e+00 2.51000000e-02 0.00000000e+00 +-1.40000000e+01 -1.07930000e+00 2.27000000e-02 0.00000000e+00 +-1.30000000e+01 -1.08040000e+00 2.06000000e-02 0.00000000e+00 +-1.20000000e+01 -1.06640000e+00 1.87000000e-02 0.00000000e+00 +-1.10000000e+01 -1.02840000e+00 1.70000000e-02 0.00000000e+00 +-1.00000000e+01 -9.75100000e-01 1.54000000e-02 0.00000000e+00 +-9.00000000e+00 -9.06700000e-01 1.39000000e-02 0.00000000e+00 +-8.00000000e+00 -8.25600000e-01 1.26000000e-02 0.00000000e+00 +-7.00000000e+00 -7.36200000e-01 1.15000000e-02 0.00000000e+00 +-6.00000000e+00 -6.60000000e-01 1.02000000e-02 0.00000000e+00 +-5.00000000e+00 -5.50000000e-01 9.50000000e-03 0.00000000e+00 +-4.00000000e+00 -4.40000000e-01 8.90000000e-03 0.00000000e+00 +-3.00000000e+00 -3.30000000e-01 8.60000000e-03 0.00000000e+00 +-2.00000000e+00 -2.20000000e-01 8.30000000e-03 0.00000000e+00 +-1.00000000e+00 -1.10000000e-01 8.20000000e-03 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 8.20000000e-03 0.00000000e+00 + 1.00000000e+00 1.10000000e-01 8.20000000e-03 0.00000000e+00 + 2.00000000e+00 2.20000000e-01 8.30000000e-03 0.00000000e+00 + 3.00000000e+00 3.30000000e-01 8.60000000e-03 0.00000000e+00 + 4.00000000e+00 4.40000000e-01 8.90000000e-03 0.00000000e+00 + 5.00000000e+00 5.50000000e-01 9.50000000e-03 0.00000000e+00 + 6.00000000e+00 6.60000000e-01 1.02000000e-02 0.00000000e+00 + 7.00000000e+00 7.36200000e-01 1.15000000e-02 0.00000000e+00 + 8.00000000e+00 8.25600000e-01 1.26000000e-02 0.00000000e+00 + 9.00000000e+00 9.06700000e-01 1.39000000e-02 0.00000000e+00 + 1.00000000e+01 9.75100000e-01 1.54000000e-02 0.00000000e+00 + 1.10000000e+01 1.02840000e+00 1.70000000e-02 0.00000000e+00 + 1.20000000e+01 1.06640000e+00 1.87000000e-02 0.00000000e+00 + 1.30000000e+01 1.08040000e+00 2.06000000e-02 0.00000000e+00 + 1.40000000e+01 1.07930000e+00 2.27000000e-02 0.00000000e+00 + 1.50000000e+01 1.06240000e+00 2.51000000e-02 0.00000000e+00 + 1.60000000e+01 1.04020000e+00 1.08000000e-01 0.00000000e+00 + 1.80000000e+01 9.95900000e-01 2.38000000e-01 0.00000000e+00 + 2.00000000e+01 9.70700000e-01 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 9.69600000e-01 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 1.01070000e+00 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +! ------------------------------------------------------------------------------ +! data for table 9 +! ------------------------------------------------------------------------------ +2.0 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +20.027374578257152 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-20.027374578257152 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.151 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.151 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0077 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +105 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -1.14680000e+00 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -1.11270000e+00 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -1.11720000e+00 2.82000000e-01 0.00000000e+00 +-1.80000000e+01 -1.13830000e+00 2.38000000e-01 0.00000000e+00 +-1.70000000e+01 -1.15500000e+00 1.20000000e-01 0.00000000e+00 +-1.60000000e+01 -1.16950000e+00 2.40000000e-02 0.00000000e+00 +-1.50000000e+01 -1.18130000e+00 2.18000000e-02 0.00000000e+00 +-1.40000000e+01 -1.18130000e+00 1.97000000e-02 0.00000000e+00 +-1.30000000e+01 -1.16620000e+00 1.79000000e-02 0.00000000e+00 +-1.20000000e+01 -1.12960000e+00 1.63000000e-02 0.00000000e+00 +-1.10000000e+01 -1.07720000e+00 1.48000000e-02 0.00000000e+00 +-1.00000000e+01 -1.01110000e+00 1.34000000e-02 0.00000000e+00 +-9.00000000e+00 -9.31400000e-01 1.22000000e-02 0.00000000e+00 +-8.00000000e+00 -8.43900000e-01 1.11000000e-02 0.00000000e+00 +-7.00000000e+00 -7.44900000e-01 1.01000000e-02 0.00000000e+00 +-6.00000000e+00 -6.60000000e-01 9.30000000e-03 0.00000000e+00 +-5.00000000e+00 -5.50000000e-01 8.70000000e-03 0.00000000e+00 +-4.00000000e+00 -4.40000000e-01 8.40000000e-03 0.00000000e+00 +-3.00000000e+00 -3.30000000e-01 8.00000000e-03 0.00000000e+00 +-2.00000000e+00 -2.20000000e-01 7.80000000e-03 0.00000000e+00 +-1.00000000e+00 -1.10000000e-01 7.70000000e-03 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 7.70000000e-03 0.00000000e+00 + 1.00000000e+00 1.10000000e-01 7.70000000e-03 0.00000000e+00 + 2.00000000e+00 2.20000000e-01 7.80000000e-03 0.00000000e+00 + 3.00000000e+00 3.30000000e-01 8.00000000e-03 0.00000000e+00 + 4.00000000e+00 4.40000000e-01 8.40000000e-03 0.00000000e+00 + 5.00000000e+00 5.50000000e-01 8.70000000e-03 0.00000000e+00 + 6.00000000e+00 6.60000000e-01 9.30000000e-03 0.00000000e+00 + 7.00000000e+00 7.44900000e-01 1.01000000e-02 0.00000000e+00 + 8.00000000e+00 8.43900000e-01 1.11000000e-02 0.00000000e+00 + 9.00000000e+00 9.31400000e-01 1.22000000e-02 0.00000000e+00 + 1.00000000e+01 1.01110000e+00 1.34000000e-02 0.00000000e+00 + 1.10000000e+01 1.07720000e+00 1.48000000e-02 0.00000000e+00 + 1.20000000e+01 1.12960000e+00 1.63000000e-02 0.00000000e+00 + 1.30000000e+01 1.16620000e+00 1.79000000e-02 0.00000000e+00 + 1.40000000e+01 1.18130000e+00 1.97000000e-02 0.00000000e+00 + 1.50000000e+01 1.18130000e+00 2.18000000e-02 0.00000000e+00 + 1.60000000e+01 1.16950000e+00 2.40000000e-02 0.00000000e+00 + 1.70000000e+01 1.15500000e+00 1.20000000e-01 0.00000000e+00 + 1.80000000e+01 1.13830000e+00 2.38000000e-01 0.00000000e+00 + 2.00000000e+01 1.11720000e+00 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 1.11270000e+00 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 1.14680000e+00 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +! ------------------------------------------------------------------------------ +! data for table 10 +! ------------------------------------------------------------------------------ +5.0 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +23.403123375221707 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-23.403123375221707 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.2617 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.2617 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0073 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +107 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -1.29250000e+00 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -1.27140000e+00 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -1.27680000e+00 2.82000000e-01 0.00000000e+00 +-1.90000000e+01 -1.28530000e+00 1.40000000e-01 0.00000000e+00 +-1.80000000e+01 -1.29600000e+00 2.44000000e-02 0.00000000e+00 +-1.70000000e+01 -1.30380000e+00 2.23000000e-02 0.00000000e+00 +-1.60000000e+01 -1.30670000e+00 2.03000000e-02 0.00000000e+00 +-1.50000000e+01 -1.30040000e+00 1.85000000e-02 0.00000000e+00 +-1.40000000e+01 -1.28080000e+00 1.68000000e-02 0.00000000e+00 +-1.30000000e+01 -1.24300000e+00 1.53000000e-02 0.00000000e+00 +-1.20000000e+01 -1.18840000e+00 1.40000000e-02 0.00000000e+00 +-1.10000000e+01 -1.12110000e+00 1.28000000e-02 0.00000000e+00 +-1.00000000e+01 -1.04040000e+00 1.17000000e-02 0.00000000e+00 +-9.00000000e+00 -9.52500000e-01 1.08000000e-02 0.00000000e+00 +-8.00000000e+00 -8.53800000e-01 1.00000000e-02 0.00000000e+00 +-7.00000000e+00 -7.70000000e-01 9.30000000e-03 0.00000000e+00 +-6.00000000e+00 -6.60000000e-01 8.70000000e-03 0.00000000e+00 +-5.00000000e+00 -5.50000000e-01 8.30000000e-03 0.00000000e+00 +-4.00000000e+00 -4.40000000e-01 7.90000000e-03 0.00000000e+00 +-3.00000000e+00 -3.30000000e-01 7.70000000e-03 0.00000000e+00 +-2.00000000e+00 -2.20000000e-01 7.50000000e-03 0.00000000e+00 +-1.00000000e+00 -1.10000000e-01 7.30000000e-03 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 7.30000000e-03 0.00000000e+00 + 1.00000000e+00 1.10000000e-01 7.30000000e-03 0.00000000e+00 + 2.00000000e+00 2.20000000e-01 7.50000000e-03 0.00000000e+00 + 3.00000000e+00 3.30000000e-01 7.70000000e-03 0.00000000e+00 + 4.00000000e+00 4.40000000e-01 7.90000000e-03 0.00000000e+00 + 5.00000000e+00 5.50000000e-01 8.30000000e-03 0.00000000e+00 + 6.00000000e+00 6.60000000e-01 8.70000000e-03 0.00000000e+00 + 7.00000000e+00 7.70000000e-01 9.30000000e-03 0.00000000e+00 + 8.00000000e+00 8.53800000e-01 1.00000000e-02 0.00000000e+00 + 9.00000000e+00 9.52500000e-01 1.08000000e-02 0.00000000e+00 + 1.00000000e+01 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Stall Model - Positive Stall AOA (deg): 1.0 -BV Dyn. Stall Model - Negative Stall AOA (deg): -1.0 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 5.73 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1 -AOA (deg) CL CD Cm25 --180 0 0.0250000000000000 0 --175 0.660000000000000 0.0550000000000000 0 --170 0.850000000000000 0.140000000000000 0 --165 0.680000000000000 0.230000000000000 0 --160 0.635000000000000 0.320000000000000 0 --155 0.670000000000000 0.420000000000000 0 --150 0.770000000000000 0.575000000000000 0 --145 0.900000000000000 0.755000000000000 0 --140 0.980000000000000 0.925000000000000 0 --135 0.930000000000000 1.08500000000000 0 --130 0.850000000000000 1.22500000000000 0 --125 0.760000000000000 1.35000000000000 0 --120 0.670000000000000 1.46500000000000 0 --115 0.575000000000000 1.55500000000000 0 --110 0.450000000000000 1.63500000000000 0 --105 0.320000000000000 1.70000000000000 0 --100 0.185000000000000 1.75000000000000 0 --95 0.0500000000000000 1.78000000000000 0 --90 -0.0900000000000000 1.80000000000000 0 --85 -0.230000000000000 1.80000000000000 0 --80 -0.365000000000000 1.78000000000000 0 --75 -0.500000000000000 1.73500000000000 0 --70 -0.630000000000000 1.66500000000000 0 --65 -0.760000000000000 1.57500000000000 0 --60 -0.875000000000000 1.47000000000000 0 --55 -0.955000000000000 1.34500000000000 0 --50 -1.02000000000000 1.21500000000000 0 --45 -1.05000000000000 1.07500000000000 0 --40 -1.03500000000000 0.920000000000000 0 --35 -0.980000000000000 0.745000000000000 0 --30 -0.855000000000000 0.570000000000000 0 --25 -0.453900000000000 0.405000000000000 0 --22 -0.300200000000000 0.329000000000000 0 --20 -0.200600000000000 0.282000000000000 0 --18 -0.103500000000000 0.238000000000000 0 --16 -0.0123000000000000 0.196000000000000 0 --14 0.0658000000000000 0.158000000000000 0 --12 0.127600000000000 0.123000000000000 0 --10 0.158100000000000 0.0750000000000000 0 --9 0.158100000000000 0.0575000000000000 0 --8 0.147500000000000 0.0538000000000000 0 --7 0.140000000000000 0.0507000000000000 0 --6 0.124000000000000 0.0480000000000000 0 --5 0.115600000000000 0.0459000000000000 0 --4 0.0995000000000000 0.0441000000000000 0 --3 0.0854000000000000 0.0429000000000000 0 --2 0.0631000000000000 0.0420000000000000 0 --1 0.0320000000000000 0.0414000000000000 0 -0 0 0.0413000000000000 0 -1 -0.0320000000000000 0.0414000000000000 0 -2 -0.0631000000000000 0.0420000000000000 0 -3 -0.0854000000000000 0.0429000000000000 0 -4 -0.0995000000000000 0.0441000000000000 0 -5 -0.115600000000000 0.0459000000000000 0 -6 -0.124000000000000 0.0480000000000000 0 -7 -0.140000000000000 0.0507000000000000 0 -8 -0.147500000000000 0.0538000000000000 0 -9 -0.158100000000000 0.0575000000000000 0 -10 -0.158100000000000 0.0750000000000000 0 -12 -0.127600000000000 0.123000000000000 0 -14 -0.0658000000000000 0.158000000000000 0 -16 0.0123000000000000 0.196000000000000 0 -18 0.103500000000000 0.238000000000000 0 -20 0.200600000000000 0.282000000000000 0 -22 0.300200000000000 0.329000000000000 0 -25 0.453900000000000 0.405000000000000 0 -30 0.855000000000000 0.570000000000000 0 -35 0.980000000000000 0.745000000000000 0 -40 1.03500000000000 0.920000000000000 0 -45 1.05000000000000 1.07500000000000 0 -50 1.02000000000000 1.21500000000000 0 -55 0.955000000000000 1.34500000000000 0 -60 0.875000000000000 1.47000000000000 0 -65 0.760000000000000 1.57500000000000 0 -70 0.630000000000000 1.66500000000000 0 -75 0.500000000000000 1.73500000000000 0 -80 0.365000000000000 1.78000000000000 0 -85 0.230000000000000 1.80000000000000 0 -90 0.0900000000000000 1.80000000000000 0 -95 -0.0500000000000000 1.78000000000000 0 -100 -0.185000000000000 1.75000000000000 0 -105 -0.320000000000000 1.70000000000000 0 -110 -0.450000000000000 1.63500000000000 0 -115 -0.575000000000000 1.55500000000000 0 -120 -0.670000000000000 1.46500000000000 0 -125 -0.760000000000000 1.35000000000000 0 -130 -0.850000000000000 1.22500000000000 0 -135 -0.930000000000000 1.08500000000000 0 -140 -0.980000000000000 0.925000000000000 0 -145 -0.900000000000000 0.755000000000000 0 -150 -0.770000000000000 0.575000000000000 0 -155 -0.670000000000000 0.420000000000000 0 -160 -0.635000000000000 0.320000000000000 0 -165 -0.680000000000000 0.230000000000000 0 -170 -0.850000000000000 0.140000000000000 0 -175 -0.660000000000000 0.0550000000000000 0 -180 0 0.0250000000000000 0 - -Reynolds Number: 2e4 -BV Dyn. Stall Model - Positive Stall AOA (deg): 1.0 -BV Dyn. Stall Model - Negative Stall AOA (deg): -1.0 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 5.73 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1 -AOA (deg) CL CD Cm25 --180 0 0.0250000000000000 0 --175 0.660000000000000 0.0550000000000000 0 --170 0.850000000000000 0.140000000000000 0 --165 0.680000000000000 0.230000000000000 0 --160 0.635000000000000 0.320000000000000 0 --155 0.670000000000000 0.420000000000000 0 --150 0.770000000000000 0.575000000000000 0 --145 0.900000000000000 0.755000000000000 0 --140 0.980000000000000 0.925000000000000 0 --135 0.930000000000000 1.08500000000000 0 --130 0.850000000000000 1.22500000000000 0 --125 0.760000000000000 1.35000000000000 0 --120 0.670000000000000 1.46500000000000 0 --115 0.575000000000000 1.55500000000000 0 --110 0.450000000000000 1.63500000000000 0 --105 0.320000000000000 1.70000000000000 0 --100 0.185000000000000 1.75000000000000 0 --95 0.0500000000000000 1.78000000000000 0 --90 -0.0900000000000000 1.80000000000000 0 --85 -0.230000000000000 1.80000000000000 0 --80 -0.365000000000000 1.78000000000000 0 --75 -0.500000000000000 1.73500000000000 0 --70 -0.630000000000000 1.66500000000000 0 --65 -0.760000000000000 1.57500000000000 0 --60 -0.875000000000000 1.47000000000000 0 --55 -0.955000000000000 1.34500000000000 0 --50 -1.02000000000000 1.21500000000000 0 --45 -1.05000000000000 1.07500000000000 0 --40 -1.03500000000000 0.920000000000000 0 --35 -0.980000000000000 0.745000000000000 0 --30 -0.855000000000000 0.570000000000000 0 --25 -0.461800000000000 0.405000000000000 0 --22 -0.310300000000000 0.329000000000000 0 --20 -0.212400000000000 0.282000000000000 0 --18 -0.118000000000000 0.238000000000000 0 --16 -0.0331000000000000 0.196000000000000 0 --14 0.0362000000000000 0.158000000000000 0 --12 0.0713000000000000 0.123000000000000 0 --10 0.0506000000000000 0.0700000000000000 0 --9 0.0190000000000000 0.0435000000000000 0 --8 -0.0120000000000000 0.0407000000000000 0 --7 -0.0266000000000000 0.0382000000000000 0 --6 -0.0475000000000000 0.0362000000000000 0 --5 -0.0505000000000000 0.0345000000000000 0 --4 -0.0619000000000000 0.0332000000000000 0 --3 -0.0472000000000000 0.0321000000000000 0 --2 -0.0393000000000000 0.0314000000000000 0 --1 -0.0243000000000000 0.0310000000000000 0 -0 0 0.0309000000000000 0 -1 0.0243000000000000 0.0310000000000000 0 -2 0.0393000000000000 0.0314000000000000 0 -3 0.0472000000000000 0.0321000000000000 0 -4 0.0619000000000000 0.0332000000000000 0 -5 0.0505000000000000 0.0345000000000000 0 -6 0.0475000000000000 0.0362000000000000 0 -7 0.0266000000000000 0.0382000000000000 0 -8 0.0120000000000000 0.0407000000000000 0 -9 -0.0190000000000000 0.0435000000000000 0 -10 -0.0506000000000000 0.0700000000000000 0 -12 -0.0713000000000000 0.123000000000000 0 -14 -0.0362000000000000 0.158000000000000 0 -16 0.0331000000000000 0.196000000000000 0 -18 0.118000000000000 0.238000000000000 0 -20 0.212400000000000 0.282000000000000 0 -22 0.310300000000000 0.329000000000000 0 -25 0.461800000000000 0.405000000000000 0 -30 0.855000000000000 0.570000000000000 0 -35 0.980000000000000 0.745000000000000 0 -40 1.03500000000000 0.920000000000000 0 -45 1.05000000000000 1.07500000000000 0 -50 1.02000000000000 1.21500000000000 0 -55 0.955000000000000 1.34500000000000 0 -60 0.875000000000000 1.47000000000000 0 -65 0.760000000000000 1.57500000000000 0 -70 0.630000000000000 1.66500000000000 0 -75 0.500000000000000 1.73500000000000 0 -80 0.365000000000000 1.78000000000000 0 -85 0.230000000000000 1.80000000000000 0 -90 0.0900000000000000 1.80000000000000 0 -95 -0.0500000000000000 1.78000000000000 0 -100 -0.185000000000000 1.75000000000000 0 -105 -0.320000000000000 1.70000000000000 0 -110 -0.450000000000000 1.63500000000000 0 -115 -0.575000000000000 1.55500000000000 0 -120 -0.670000000000000 1.46500000000000 0 -125 -0.760000000000000 1.35000000000000 0 -130 -0.850000000000000 1.22500000000000 0 -135 -0.930000000000000 1.08500000000000 0 -140 -0.980000000000000 0.925000000000000 0 -145 -0.900000000000000 0.755000000000000 0 -150 -0.770000000000000 0.575000000000000 0 -155 -0.670000000000000 0.420000000000000 0 -160 -0.635000000000000 0.320000000000000 0 -165 -0.680000000000000 0.230000000000000 0 -170 -0.850000000000000 0.140000000000000 0 -175 -0.660000000000000 0.0550000000000000 0 -180 0 0.0250000000000000 0 - -Reynolds Number: 4e4 -BV Dyn. Stall Model - Positive Stall AOA (deg): 3.0 -BV Dyn. Stall Model - Negative Stall AOA (deg): -3.0 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 4.309 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 0.526 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -0.526 -AOA (deg) CL CD Cm25 --180 0 0.0250000000000000 0 --175 0.660000000000000 0.0550000000000000 0 --170 0.850000000000000 0.140000000000000 0 --165 0.680000000000000 0.230000000000000 0 --160 0.635000000000000 0.320000000000000 0 --155 0.670000000000000 0.420000000000000 0 --150 0.770000000000000 0.575000000000000 0 --145 0.900000000000000 0.755000000000000 0 --140 0.980000000000000 0.925000000000000 0 --135 0.930000000000000 1.08500000000000 0 --130 0.850000000000000 1.22500000000000 0 --125 0.760000000000000 1.35000000000000 0 --120 0.670000000000000 1.46500000000000 0 --115 0.575000000000000 1.55500000000000 0 --110 0.450000000000000 1.63500000000000 0 --105 0.320000000000000 1.70000000000000 0 --100 0.185000000000000 1.75000000000000 0 --95 0.0500000000000000 1.78000000000000 0 --90 -0.0900000000000000 1.80000000000000 0 --85 -0.230000000000000 1.80000000000000 0 --80 -0.365000000000000 1.78000000000000 0 --75 -0.500000000000000 1.73500000000000 0 --70 -0.630000000000000 1.66500000000000 0 --65 -0.760000000000000 1.57500000000000 0 --60 -0.875000000000000 1.47000000000000 0 --55 -0.955000000000000 1.34500000000000 0 --50 -1.02000000000000 1.21500000000000 0 --45 -1.05000000000000 1.07500000000000 0 --40 -1.03500000000000 0.920000000000000 0 --35 -0.980000000000000 0.745000000000000 0 --30 -0.855000000000000 0.570000000000000 0 --25 -0.480200000000000 0.405000000000000 0 --22 -0.334500000000000 0.329000000000000 0 --20 -0.241400000000000 0.282000000000000 0 --18 -0.161900000000000 0.238000000000000 0 --16 -0.0981000000000000 0.196000000000000 0 --14 -0.0833000000000000 0.158000000000000 0 --12 -0.166000000000000 0.123000000000000 0 --10 -0.269100000000000 0.0620000000000000 0 --9 -0.316200000000000 0.0343000000000000 0 --8 -0.342000000000000 0.0319000000000000 0 --7 -0.342700000000000 0.0297000000000000 0 --6 -0.338200000000000 0.0279000000000000 0 --5 -0.308600000000000 0.0264000000000000 0 --4 -0.273000000000000 0.0253000000000000 0 --3 -0.210300000000000 0.0243000000000000 0 --2 -0.146500000000000 0.0237000000000000 0 --1 -0.0752000000000000 0.0233000000000000 0 -0 0 0.0232000000000000 0 -1 0.0752000000000000 0.0233000000000000 0 -2 0.146500000000000 0.0237000000000000 0 -3 0.210300000000000 0.0243000000000000 0 -4 0.273000000000000 0.0253000000000000 0 -5 0.308600000000000 0.0264000000000000 0 -6 0.338200000000000 0.0279000000000000 0 -7 0.342700000000000 0.0297000000000000 0 -8 0.342000000000000 0.0319000000000000 0 -9 0.316200000000000 0.0343000000000000 0 -10 0.269100000000000 0.0620000000000000 0 -12 0.166000000000000 0.123000000000000 0 -14 0.0833000000000000 0.158000000000000 0 -16 0.0981000000000000 0.196000000000000 0 -18 0.161900000000000 0.238000000000000 0 -20 0.241400000000000 0.282000000000000 0 -22 0.334500000000000 0.329000000000000 0 -25 0.480200000000000 0.405000000000000 0 -30 0.855000000000000 0.570000000000000 0 -35 0.980000000000000 0.745000000000000 0 -40 1.03500000000000 0.920000000000000 0 -45 1.05000000000000 1.07500000000000 0 -50 1.02000000000000 1.21500000000000 0 -55 0.955000000000000 1.34500000000000 0 -60 0.875000000000000 1.47000000000000 0 -65 0.760000000000000 1.57500000000000 0 -70 0.630000000000000 1.66500000000000 0 -75 0.500000000000000 1.73500000000000 0 -80 0.365000000000000 1.78000000000000 0 -85 0.230000000000000 1.80000000000000 0 -90 0.0900000000000000 1.80000000000000 0 -95 -0.0500000000000000 1.78000000000000 0 -100 -0.185000000000000 1.75000000000000 0 -105 -0.320000000000000 1.70000000000000 0 -110 -0.450000000000000 1.63500000000000 0 -115 -0.575000000000000 1.55500000000000 0 -120 -0.670000000000000 1.46500000000000 0 -125 -0.760000000000000 1.35000000000000 0 -130 -0.850000000000000 1.22500000000000 0 -135 -0.930000000000000 1.08500000000000 0 -140 -0.980000000000000 0.925000000000000 0 -145 -0.900000000000000 0.755000000000000 0 -150 -0.770000000000000 0.575000000000000 0 -155 -0.670000000000000 0.420000000000000 0 -160 -0.635000000000000 0.320000000000000 0 -165 -0.680000000000000 0.230000000000000 0 -170 -0.850000000000000 0.140000000000000 0 -175 -0.660000000000000 0.0550000000000000 0 -180 0 0.0250000000000000 0 - -Reynolds Number: 8e4 -BV Dyn. Stall Model - Positive Stall AOA (deg): 4.0 -BV Dyn. Stall Model - Negative Stall AOA (deg): -4.0 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 5.277 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 0.829 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -0.829 -AOA (deg) CL CD Cm25 --180 0 0.0250000000000000 0 --175 0.660000000000000 0.0550000000000000 0 --170 0.850000000000000 0.140000000000000 0 --165 0.680000000000000 0.230000000000000 0 --160 0.635000000000000 0.320000000000000 0 --155 0.670000000000000 0.420000000000000 0 --150 0.770000000000000 0.575000000000000 0 --145 0.900000000000000 0.755000000000000 0 --140 0.980000000000000 0.925000000000000 0 --135 0.930000000000000 1.08500000000000 0 --130 0.850000000000000 1.22500000000000 0 --125 0.760000000000000 1.35000000000000 0 --120 0.670000000000000 1.46500000000000 0 --115 0.575000000000000 1.55500000000000 0 --110 0.450000000000000 1.63500000000000 0 --105 0.320000000000000 1.70000000000000 0 --100 0.185000000000000 1.75000000000000 0 --95 0.0500000000000000 1.78000000000000 0 --90 -0.0900000000000000 1.80000000000000 0 --85 -0.230000000000000 1.80000000000000 0 --80 -0.365000000000000 1.78000000000000 0 --75 -0.500000000000000 1.73500000000000 0 --70 -0.630000000000000 1.66500000000000 0 --65 -0.760000000000000 1.57500000000000 0 --60 -0.875000000000000 1.47000000000000 0 --55 -0.955000000000000 1.34500000000000 0 --50 -1.02000000000000 1.21500000000000 0 --45 -1.05000000000000 1.07500000000000 0 --40 -1.03500000000000 0.920000000000000 0 --35 -0.980000000000000 0.745000000000000 0 --30 -0.855000000000000 0.570000000000000 0 --25 -0.529700000000000 0.405000000000000 0 --22 -0.409100000000000 0.329000000000000 0 --20 -0.347500000000000 0.282000000000000 0 --18 -0.322100000000000 0.238000000000000 0 --16 -0.349900000000000 0.196000000000000 0 --14 -0.429600000000000 0.158000000000000 0 --12 -0.522800000000000 0.123000000000000 0 --11 -0.556400000000000 0.0700000000000000 0 --10 -0.578000000000000 0.0297000000000000 0 --9 -0.587400000000000 0.0273000000000000 0 --8 -0.575100000000000 0.0252000000000000 0 --7 -0.544500000000000 0.0233000000000000 0 --6 -0.495300000000000 0.0217000000000000 0 --5 -0.432400000000000 0.0204000000000000 0 --4 -0.356400000000000 0.0194000000000000 0 --3 -0.273100000000000 0.0186000000000000 0 --2 -0.183900000000000 0.0181000000000000 0 --1 -0.0921000000000000 0.0178000000000000 0 -0 0 0.0177000000000000 0 -1 0.0921000000000000 0.0178000000000000 0 -2 0.183900000000000 0.0181000000000000 0 -3 0.273100000000000 0.0186000000000000 0 -4 0.356400000000000 0.0194000000000000 0 -5 0.432400000000000 0.0204000000000000 0 -6 0.495300000000000 0.0217000000000000 0 -7 0.544500000000000 0.0233000000000000 0 -8 0.575100000000000 0.0252000000000000 0 -9 0.587400000000000 0.0273000000000000 0 -10 0.578000000000000 0.0297000000000000 0 -11 0.556400000000000 0.0700000000000000 0 -12 0.522800000000000 0.123000000000000 0 -14 0.429600000000000 0.158000000000000 0 -16 0.349900000000000 0.196000000000000 0 -18 0.322100000000000 0.238000000000000 0 -20 0.347500000000000 0.282000000000000 0 -22 0.409100000000000 0.329000000000000 0 -25 0.529700000000000 0.405000000000000 0 -30 0.855000000000000 0.570000000000000 0 -35 0.980000000000000 0.745000000000000 0 -40 1.03500000000000 0.920000000000000 0 -45 1.05000000000000 1.07500000000000 0 -50 1.02000000000000 1.21500000000000 0 -55 0.955000000000000 1.34500000000000 0 -60 0.875000000000000 1.47000000000000 0 -65 0.760000000000000 1.57500000000000 0 -70 0.630000000000000 1.66500000000000 0 -75 0.500000000000000 1.73500000000000 0 -80 0.365000000000000 1.78000000000000 0 -85 0.230000000000000 1.80000000000000 0 -90 0.0900000000000000 1.80000000000000 0 -95 -0.0500000000000000 1.78000000000000 0 -100 -0.185000000000000 1.75000000000000 0 -105 -0.320000000000000 1.70000000000000 0 -110 -0.450000000000000 1.63500000000000 0 -115 -0.575000000000000 1.55500000000000 0 -120 -0.670000000000000 1.46500000000000 0 -125 -0.760000000000000 1.35000000000000 0 -130 -0.850000000000000 1.22500000000000 0 -135 -0.930000000000000 1.08500000000000 0 -140 -0.980000000000000 0.925000000000000 0 -145 -0.900000000000000 0.755000000000000 0 -150 -0.770000000000000 0.575000000000000 0 -155 -0.670000000000000 0.420000000000000 0 -160 -0.635000000000000 0.320000000000000 0 -165 -0.680000000000000 0.230000000000000 0 -170 -0.850000000000000 0.140000000000000 0 -175 -0.660000000000000 0.0550000000000000 0 -180 0 0.0250000000000000 0 - -Reynolds Number: 1.6e5 -BV Dyn. Stall Model - Positive Stall AOA (deg): 5.0 -BV Dyn. Stall Model - Negative Stall AOA (deg): -5.0 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 5.371 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.031 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.031 -AOA (deg) CL CD Cm25 --180 0 0.0250000000000000 0 --175 0.660000000000000 0.0550000000000000 0 --170 0.850000000000000 0.140000000000000 0 --165 0.680000000000000 0.230000000000000 0 --160 0.635000000000000 0.320000000000000 0 --155 0.670000000000000 0.420000000000000 0 --150 0.770000000000000 0.575000000000000 0 --145 0.900000000000000 0.755000000000000 0 --140 0.980000000000000 0.925000000000000 0 --135 0.930000000000000 1.08500000000000 0 --130 0.850000000000000 1.22500000000000 0 --125 0.760000000000000 1.35000000000000 0 --120 0.670000000000000 1.46500000000000 0 --115 0.575000000000000 1.55500000000000 0 --110 0.450000000000000 1.63500000000000 0 --105 0.320000000000000 1.70000000000000 0 --100 0.185000000000000 1.75000000000000 0 --95 0.0500000000000000 1.78000000000000 0 --90 -0.0900000000000000 1.80000000000000 0 --85 -0.230000000000000 1.80000000000000 0 --80 -0.365000000000000 1.78000000000000 0 --75 -0.500000000000000 1.73500000000000 0 --70 -0.630000000000000 1.66500000000000 0 --65 -0.760000000000000 1.57500000000000 0 --60 -0.875000000000000 1.47000000000000 0 --55 -0.955000000000000 1.34500000000000 0 --50 -1.02000000000000 1.21500000000000 0 --45 -1.05000000000000 1.07500000000000 0 --40 -1.03500000000000 0.920000000000000 0 --35 -0.980000000000000 0.745000000000000 0 --30 -0.855000000000000 0.570000000000000 0 --25 -0.666400000000000 0.405000000000000 0 --22 -0.602300000000000 0.329000000000000 0 --20 -0.592000000000000 0.282000000000000 0 --18 -0.609800000000000 0.238000000000000 0 --16 -0.648700000000000 0.196000000000000 0 --14 -0.699300000000000 0.158000000000000 0 --13 -0.725500000000000 0.0860000000000000 0 --12 -0.736300000000000 0.0292000000000000 0 --11 -0.744300000000000 0.0266000000000000 0 --10 -0.737400000000000 0.0243000000000000 0 --9 -0.714800000000000 0.0222000000000000 0 --8 -0.674500000000000 0.0204000000000000 0 --7 -0.620900000000000 0.0187000000000000 0 --6 -0.548600000000000 0.0174000000000000 0 --5 -0.468700000000000 0.0163000000000000 0 --4 -0.380000000000000 0.0155000000000000 0 --3 -0.286100000000000 0.0148000000000000 0 --2 -0.187900000000000 0.0143000000000000 0 --1 -0.0842000000000000 0.0140000000000000 0 -0 0 0.0139000000000000 0 -1 0.0842000000000000 0.0140000000000000 0 -2 0.187900000000000 0.0143000000000000 0 -3 0.286100000000000 0.0148000000000000 0 -4 0.380000000000000 0.0155000000000000 0 -5 0.468700000000000 0.0163000000000000 0 -6 0.548600000000000 0.0174000000000000 0 -7 0.620900000000000 0.0187000000000000 0 -8 0.674500000000000 0.0204000000000000 0 -9 0.714800000000000 0.0222000000000000 0 -10 0.737400000000000 0.0243000000000000 0 -11 0.744300000000000 0.0266000000000000 0 -12 0.736300000000000 0.0292000000000000 0 -13 0.725500000000000 0.0860000000000000 0 -14 0.699300000000000 0.158000000000000 0 -16 0.648700000000000 0.196000000000000 0 -18 0.609800000000000 0.238000000000000 0 -20 0.592000000000000 0.282000000000000 0 -22 0.602300000000000 0.329000000000000 0 -25 0.666400000000000 0.405000000000000 0 -30 0.855000000000000 0.570000000000000 0 -35 0.980000000000000 0.745000000000000 0 -40 1.03500000000000 0.920000000000000 0 -45 1.05000000000000 1.07500000000000 0 -50 1.02000000000000 1.21500000000000 0 -55 0.955000000000000 1.34500000000000 0 -60 0.875000000000000 1.47000000000000 0 -65 0.760000000000000 1.57500000000000 0 -70 0.630000000000000 1.66500000000000 0 -75 0.500000000000000 1.73500000000000 0 -80 0.365000000000000 1.78000000000000 0 -85 0.230000000000000 1.80000000000000 0 -90 0.0900000000000000 1.80000000000000 0 -95 -0.0500000000000000 1.78000000000000 0 -100 -0.185000000000000 1.75000000000000 0 -105 -0.320000000000000 1.70000000000000 0 -110 -0.450000000000000 1.63500000000000 0 -115 -0.575000000000000 1.55500000000000 0 -120 -0.670000000000000 1.46500000000000 0 -125 -0.760000000000000 1.35000000000000 0 -130 -0.850000000000000 1.22500000000000 0 -135 -0.930000000000000 1.08500000000000 0 -140 -0.980000000000000 0.925000000000000 0 -145 -0.900000000000000 0.755000000000000 0 -150 -0.770000000000000 0.575000000000000 0 -155 -0.670000000000000 0.420000000000000 0 -160 -0.635000000000000 0.320000000000000 0 -165 -0.680000000000000 0.230000000000000 0 -170 -0.850000000000000 0.140000000000000 0 -175 -0.660000000000000 0.0550000000000000 0 -180 0 0.0250000000000000 0 - -Reynolds Number: 3.6e5 -BV Dyn. Stall Model - Positive Stall AOA (deg): 5.0 -BV Dyn. Stall Model - Negative Stall AOA (deg): -5.0 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.32 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.32 -AOA (deg) CL CD Cm25 --180 0 0.0250000000000000 0 --175 0.660000000000000 0.0550000000000000 0 --170 0.850000000000000 0.140000000000000 0 --165 0.680000000000000 0.230000000000000 0 --160 0.635000000000000 0.320000000000000 0 --155 0.670000000000000 0.420000000000000 0 --150 0.770000000000000 0.575000000000000 0 --145 0.900000000000000 0.755000000000000 0 --140 0.980000000000000 0.925000000000000 0 --135 0.930000000000000 1.08500000000000 0 --130 0.850000000000000 1.22500000000000 0 --125 0.760000000000000 1.35000000000000 0 --120 0.670000000000000 1.46500000000000 0 --115 0.575000000000000 1.55500000000000 0 --110 0.450000000000000 1.63500000000000 0 --105 0.320000000000000 1.70000000000000 0 --100 0.185000000000000 1.75000000000000 0 --95 0.0500000000000000 1.78000000000000 0 --90 -0.0900000000000000 1.80000000000000 0 --85 -0.230000000000000 1.80000000000000 0 --80 -0.365000000000000 1.78000000000000 0 --75 -0.500000000000000 1.73500000000000 0 --70 -0.630000000000000 1.66500000000000 0 --65 -0.760000000000000 1.57500000000000 0 --60 -0.875000000000000 1.47000000000000 0 --55 -0.955000000000000 1.34500000000000 0 --50 -1.02000000000000 1.21500000000000 0 --45 -1.05000000000000 1.07500000000000 0 --40 -1.03500000000000 0.920000000000000 0 --35 -0.980000000000000 0.745000000000000 0 --30 -0.855000000000000 0.570000000000000 0 --25 -0.886600000000000 0.405000000000000 0 --22 -0.845300000000000 0.329000000000000 0 --20 -0.839700000000000 0.282000000000000 0 --18 -0.848900000000000 0.238000000000000 0 --16 -0.871700000000000 0.196000000000000 0 --15 -0.884000000000000 0.104000000000000 0 --14 -0.893700000000000 0.0286000000000000 0 --13 -0.897300000000000 0.0260000000000000 0 --12 -0.893800000000000 0.0237000000000000 0 --11 -0.877900000000000 0.0215000000000000 0 --10 -0.850000000000000 0.0195000000000000 0 --9 -0.802600000000000 0.0178000000000000 0 --8 -0.743400000000000 0.0163000000000000 0 --7 -0.672800000000000 0.0149000000000000 0 --6 -0.589100000000000 0.0138000000000000 0 --5 -0.499800000000000 0.0129000000000000 0 --4 -0.404400000000000 0.0122000000000000 0 --3 -0.302400000000000 0.0117000000000000 0 --2 -0.220000000000000 0.0113000000000000 0 --1 -0.110000000000000 0.0111000000000000 0 -0 0 0.0111000000000000 0 -1 0.110000000000000 0.0111000000000000 0 -2 0.220000000000000 0.0113000000000000 0 -3 0.302400000000000 0.0117000000000000 0 -4 0.404400000000000 0.0122000000000000 0 -5 0.499800000000000 0.0129000000000000 0 -6 0.589100000000000 0.0138000000000000 0 -7 0.672800000000000 0.0149000000000000 0 -8 0.743400000000000 0.0163000000000000 0 -9 0.802600000000000 0.0178000000000000 0 -10 0.850000000000000 0.0195000000000000 0 -11 0.877900000000000 0.0215000000000000 0 -12 0.893800000000000 0.0237000000000000 0 -13 0.897300000000000 0.0260000000000000 0 -14 0.893700000000000 0.0286000000000000 0 -15 0.884000000000000 0.104000000000000 0 -16 0.871700000000000 0.196000000000000 0 -18 0.848900000000000 0.238000000000000 0 -20 0.839700000000000 0.282000000000000 0 -22 0.845300000000000 0.329000000000000 0 -25 0.886600000000000 0.405000000000000 0 -30 0.855000000000000 0.570000000000000 0 -35 0.980000000000000 0.745000000000000 0 -40 1.03500000000000 0.920000000000000 0 -45 1.05000000000000 1.07500000000000 0 -50 1.02000000000000 1.21500000000000 0 -55 0.955000000000000 1.34500000000000 0 -60 0.875000000000000 1.47000000000000 0 -65 0.760000000000000 1.57500000000000 0 -70 0.630000000000000 1.66500000000000 0 -75 0.500000000000000 1.73500000000000 0 -80 0.365000000000000 1.78000000000000 0 -85 0.230000000000000 1.80000000000000 0 -90 0.0900000000000000 1.80000000000000 0 -95 -0.0500000000000000 1.78000000000000 0 -100 -0.185000000000000 1.75000000000000 0 -105 -0.320000000000000 1.70000000000000 0 -110 -0.450000000000000 1.63500000000000 0 -115 -0.575000000000000 1.55500000000000 0 -120 -0.670000000000000 1.46500000000000 0 -125 -0.760000000000000 1.35000000000000 0 -130 -0.850000000000000 1.22500000000000 0 -135 -0.930000000000000 1.08500000000000 0 -140 -0.980000000000000 0.925000000000000 0 -145 -0.900000000000000 0.755000000000000 0 -150 -0.770000000000000 0.575000000000000 0 -155 -0.670000000000000 0.420000000000000 0 -160 -0.635000000000000 0.320000000000000 0 -165 -0.680000000000000 0.230000000000000 0 -170 -0.850000000000000 0.140000000000000 0 -175 -0.660000000000000 0.0550000000000000 0 -180 0 0.0250000000000000 0 - -Reynolds Number: 7e5 -BV Dyn. Stall Model - Positive Stall AOA (deg): 6.0 -BV Dyn. Stall Model - Negative Stall AOA (deg): -6.0 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.54 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.54 -AOA (deg) CL CD Cm25 --180 0 0.0250000000000000 0 --175 0.660000000000000 0.0550000000000000 0 --170 0.850000000000000 0.140000000000000 0 --165 0.680000000000000 0.230000000000000 0 --160 0.635000000000000 0.320000000000000 0 --155 0.670000000000000 0.420000000000000 0 --150 0.770000000000000 0.575000000000000 0 --145 0.900000000000000 0.755000000000000 0 --140 0.980000000000000 0.925000000000000 0 --135 0.930000000000000 1.08500000000000 0 --130 0.850000000000000 1.22500000000000 0 --125 0.760000000000000 1.35000000000000 0 --120 0.670000000000000 1.46500000000000 0 --115 0.575000000000000 1.55500000000000 0 --110 0.450000000000000 1.63500000000000 0 --105 0.320000000000000 1.70000000000000 0 --100 0.185000000000000 1.75000000000000 0 --95 0.0500000000000000 1.78000000000000 0 --90 -0.0900000000000000 1.80000000000000 0 --85 -0.230000000000000 1.80000000000000 0 --80 -0.365000000000000 1.78000000000000 0 --75 -0.500000000000000 1.73500000000000 0 --70 -0.630000000000000 1.66500000000000 0 --65 -0.760000000000000 1.57500000000000 0 --60 -0.875000000000000 1.47000000000000 0 --55 -0.955000000000000 1.34500000000000 0 --50 -1.02000000000000 1.21500000000000 0 --45 -1.05000000000000 1.07500000000000 0 --40 -1.03500000000000 0.920000000000000 0 --35 -0.980000000000000 0.745000000000000 0 --30 -0.855000000000000 0.570000000000000 0 --25 -1.03500000000000 0.405000000000000 0 --22 -0.994000000000000 0.329000000000000 0 --20 -0.985800000000000 0.282000000000000 0 --18 -0.991100000000000 0.238000000000000 0 --17 -0.997300000000000 0.125000000000000 0 --16 -1.00560000000000 0.0295000000000000 0 --15 -1.01060000000000 0.0269000000000000 0 --14 -1.01220000000000 0.0244000000000000 0 --13 -1.00200000000000 0.0223000000000000 0 --12 -0.984300000000000 0.0202000000000000 0 --11 -0.954300000000000 0.0184000000000000 0 --10 -0.909100000000000 0.0166000000000000 0 --9 -0.849800000000000 0.0152000000000000 0 --8 -0.780200000000000 0.0138000000000000 0 --7 -0.698800000000000 0.0126000000000000 0 --6 -0.610000000000000 0.0117000000000000 0 --5 -0.514600000000000 0.0109000000000000 0 --4 -0.412800000000000 0.0103000000000000 0 --3 -0.330000000000000 0.00980000000000000 0 --2 -0.220000000000000 0.00960000000000000 0 --1 -0.110000000000000 0.00940000000000000 0 -0 0 0.00940000000000000 0 -1 0.110000000000000 0.00940000000000000 0 -2 0.220000000000000 0.00960000000000000 0 -3 0.330000000000000 0.00980000000000000 0 -4 0.412800000000000 0.0103000000000000 0 -5 0.514600000000000 0.0109000000000000 0 -6 0.610000000000000 0.0117000000000000 0 -7 0.698800000000000 0.0126000000000000 0 -8 0.780200000000000 0.0138000000000000 0 -9 0.849800000000000 0.0152000000000000 0 -10 0.909100000000000 0.0166000000000000 0 -11 0.954300000000000 0.0184000000000000 0 -12 0.984300000000000 0.0202000000000000 0 -13 1.00200000000000 0.0223000000000000 0 -14 1.01220000000000 0.0244000000000000 0 -15 1.01060000000000 0.0269000000000000 0 -16 1.00560000000000 0.0295000000000000 0 -17 0.997300000000000 0.125000000000000 0 -18 0.991100000000000 0.238000000000000 0 -20 0.985800000000000 0.282000000000000 0 -22 0.994000000000000 0.329000000000000 0 -25 1.03500000000000 0.405000000000000 0 -30 0.855000000000000 0.570000000000000 0 -35 0.980000000000000 0.745000000000000 0 -40 1.03500000000000 0.920000000000000 0 -45 1.05000000000000 1.07500000000000 0 -50 1.02000000000000 1.21500000000000 0 -55 0.955000000000000 1.34500000000000 0 -60 0.875000000000000 1.47000000000000 0 -65 0.760000000000000 1.57500000000000 0 -70 0.630000000000000 1.66500000000000 0 -75 0.500000000000000 1.73500000000000 0 -80 0.365000000000000 1.78000000000000 0 -85 0.230000000000000 1.80000000000000 0 -90 0.0900000000000000 1.80000000000000 0 -95 -0.0500000000000000 1.78000000000000 0 -100 -0.185000000000000 1.75000000000000 0 -105 -0.320000000000000 1.70000000000000 0 -110 -0.450000000000000 1.63500000000000 0 -115 -0.575000000000000 1.55500000000000 0 -120 -0.670000000000000 1.46500000000000 0 -125 -0.760000000000000 1.35000000000000 0 -130 -0.850000000000000 1.22500000000000 0 -135 -0.930000000000000 1.08500000000000 0 -140 -0.980000000000000 0.925000000000000 0 -145 -0.900000000000000 0.755000000000000 0 -150 -0.770000000000000 0.575000000000000 0 -155 -0.670000000000000 0.420000000000000 0 -160 -0.635000000000000 0.320000000000000 0 -165 -0.680000000000000 0.230000000000000 0 -170 -0.850000000000000 0.140000000000000 0 -175 -0.660000000000000 0.0550000000000000 0 -180 0 0.0250000000000000 0 - -Reynolds Number: 1e6 -BV Dyn. Stall Model - Positive Stall AOA (deg): 6.0 -BV Dyn. Stall Model - Negative Stall AOA (deg): -6.0 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.65 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.65 -AOA (deg) CL CD Cm25 --180 0 0.0250000000000000 0 --175 0.660000000000000 0.0550000000000000 0 --170 0.850000000000000 0.140000000000000 0 --165 0.680000000000000 0.230000000000000 0 --160 0.635000000000000 0.320000000000000 0 --155 0.670000000000000 0.420000000000000 0 --150 0.770000000000000 0.575000000000000 0 --145 0.900000000000000 0.755000000000000 0 --140 0.980000000000000 0.925000000000000 0 --135 0.930000000000000 1.08500000000000 0 --130 0.850000000000000 1.22500000000000 0 --125 0.760000000000000 1.35000000000000 0 --120 0.670000000000000 1.46500000000000 0 --115 0.575000000000000 1.55500000000000 0 --110 0.450000000000000 1.63500000000000 0 --105 0.320000000000000 1.70000000000000 0 --100 0.185000000000000 1.75000000000000 0 --95 0.0500000000000000 1.78000000000000 0 --90 -0.0900000000000000 1.80000000000000 0 --85 -0.230000000000000 1.80000000000000 0 --80 -0.365000000000000 1.78000000000000 0 --75 -0.500000000000000 1.73500000000000 0 --70 -0.630000000000000 1.66500000000000 0 --65 -0.760000000000000 1.57500000000000 0 --60 -0.875000000000000 1.47000000000000 0 --55 -0.955000000000000 1.34500000000000 0 --50 -1.02000000000000 1.21500000000000 0 --45 -1.05000000000000 1.07500000000000 0 --40 -1.03500000000000 0.920000000000000 0 --35 -0.980000000000000 0.745000000000000 0 --30 -0.855000000000000 0.570000000000000 0 --25 -1.10180000000000 0.405000000000000 0 --22 -1.06440000000000 0.329000000000000 0 --20 -1.05540000000000 0.282000000000000 0 --18 -1.05880000000000 0.135000000000000 0 --17 -1.06410000000000 0.0300000000000000 0 --16 -1.06900000000000 0.0273000000000000 0 --15 -1.07090000000000 0.0248000000000000 0 --14 -1.06570000000000 0.0226000000000000 0 --13 -1.04920000000000 0.0206000000000000 0 --12 -1.02570000000000 0.0187000000000000 0 --11 -0.986200000000000 0.0170000000000000 0 --10 -0.936400000000000 0.0154000000000000 0 --9 -0.869400000000000 0.0140000000000000 0 --8 -0.793900000000000 0.0128000000000000 0 --7 -0.710200000000000 0.0117000000000000 0 --6 -0.619100000000000 0.0108000000000000 0 --5 -0.519200000000000 0.0101000000000000 0 --4 -0.440000000000000 0.00960000000000000 0 --3 -0.330000000000000 0.00920000000000000 0 --2 -0.220000000000000 0.00900000000000000 0 --1 -0.110000000000000 0.00890000000000000 0 -0 0 0.00890000000000000 0 -1 0.110000000000000 0.00890000000000000 0 -2 0.220000000000000 0.00900000000000000 0 -3 0.330000000000000 0.00920000000000000 0 -4 0.440000000000000 0.00960000000000000 0 -5 0.519200000000000 0.0101000000000000 0 -6 0.619100000000000 0.0108000000000000 0 -7 0.710200000000000 0.0117000000000000 0 -8 0.793900000000000 0.0128000000000000 0 -9 0.869400000000000 0.0140000000000000 0 -10 0.936400000000000 0.0154000000000000 0 -11 0.986200000000000 0.0170000000000000 0 -12 1.02570000000000 0.0187000000000000 0 -13 1.04920000000000 0.0206000000000000 0 -14 1.06570000000000 0.0226000000000000 0 -15 1.07090000000000 0.0248000000000000 0 -16 1.06900000000000 0.0273000000000000 0 -17 1.06410000000000 0.0300000000000000 0 -18 1.05880000000000 0.135000000000000 0 -20 1.05540000000000 0.282000000000000 0 -22 1.06440000000000 0.329000000000000 0 -25 1.10180000000000 0.405000000000000 0 -30 0.855000000000000 0.570000000000000 0 -35 0.980000000000000 0.745000000000000 0 -40 1.03500000000000 0.920000000000000 0 -45 1.05000000000000 1.07500000000000 0 -50 1.02000000000000 1.21500000000000 0 -55 0.955000000000000 1.34500000000000 0 -60 0.875000000000000 1.47000000000000 0 -65 0.760000000000000 1.57500000000000 0 -70 0.630000000000000 1.66500000000000 0 -75 0.500000000000000 1.73500000000000 0 -80 0.365000000000000 1.78000000000000 0 -85 0.230000000000000 1.80000000000000 0 -90 0.0900000000000000 1.80000000000000 0 -95 -0.0500000000000000 1.78000000000000 0 -100 -0.185000000000000 1.75000000000000 0 -105 -0.320000000000000 1.70000000000000 0 -110 -0.450000000000000 1.63500000000000 0 -115 -0.575000000000000 1.55500000000000 0 -120 -0.670000000000000 1.46500000000000 0 -125 -0.760000000000000 1.35000000000000 0 -130 -0.850000000000000 1.22500000000000 0 -135 -0.930000000000000 1.08500000000000 0 -140 -0.980000000000000 0.925000000000000 0 -145 -0.900000000000000 0.755000000000000 0 -150 -0.770000000000000 0.575000000000000 0 -155 -0.670000000000000 0.420000000000000 0 -160 -0.635000000000000 0.320000000000000 0 -165 -0.680000000000000 0.230000000000000 0 -170 -0.850000000000000 0.140000000000000 0 -175 -0.660000000000000 0.0550000000000000 0 -180 0 0.0250000000000000 0 - -Reynolds Number: 2e6 -BV Dyn. Stall Model - Positive Stall AOA (deg): 6.0 -BV Dyn. Stall Model - Negative Stall AOA (deg): -6.0 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.65 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.65 -AOA (deg) CL CD Cm25 --180 0 0.0250000000000000 0 --175 0.660000000000000 0.0550000000000000 0 --170 0.850000000000000 0.140000000000000 0 --165 0.680000000000000 0.230000000000000 0 --160 0.635000000000000 0.320000000000000 0 --155 0.670000000000000 0.420000000000000 0 --150 0.770000000000000 0.575000000000000 0 --145 0.900000000000000 0.755000000000000 0 --140 0.980000000000000 0.925000000000000 0 --135 0.930000000000000 1.08500000000000 0 --130 0.850000000000000 1.22500000000000 0 --125 0.760000000000000 1.35000000000000 0 --120 0.670000000000000 1.46500000000000 0 --115 0.575000000000000 1.55500000000000 0 --110 0.450000000000000 1.63500000000000 0 --105 0.320000000000000 1.70000000000000 0 --100 0.185000000000000 1.75000000000000 0 --95 0.0500000000000000 1.78000000000000 0 --90 -0.0900000000000000 1.80000000000000 0 --85 -0.230000000000000 1.80000000000000 0 --80 -0.365000000000000 1.78000000000000 0 --75 -0.500000000000000 1.73500000000000 0 --70 -0.630000000000000 1.66500000000000 0 --65 -0.760000000000000 1.57500000000000 0 --60 -0.875000000000000 1.47000000000000 0 --55 -0.955000000000000 1.34500000000000 0 --50 -1.02000000000000 1.21500000000000 0 --45 -1.05000000000000 1.07500000000000 0 --40 -1.03500000000000 0.920000000000000 0 --35 -0.980000000000000 0.745000000000000 0 --30 -0.855000000000000 0.570000000000000 0 --25 -1.22300000000000 0.405000000000000 0 --22 -1.18930000000000 0.329000000000000 0 --20 -1.18120000000000 0.282000000000000 0 --19 -1.17970000000000 0.145000000000000 0 --18 -1.18140000000000 0.0285000000000000 0 --17 -1.18240000000000 0.0260000000000000 0 --16 -1.18230000000000 0.0236000000000000 0 --15 -1.17470000000000 0.0215000000000000 0 --14 -1.15800000000000 0.0196000000000000 0 --13 -1.13050000000000 0.0179000000000000 0 --12 -1.09060000000000 0.0162000000000000 0 --11 -1.03980000000000 0.0148000000000000 0 --10 -0.973900000000000 0.0135000000000000 0 --9 -0.898600000000000 0.0124000000000000 0 --8 -0.814300000000000 0.0114000000000000 0 --7 -0.725400000000000 0.0105000000000000 0 --6 -0.626800000000000 0.00980000000000000 0 --5 -0.550000000000000 0.00920000000000000 0 --4 -0.440000000000000 0.00890000000000000 0 --3 -0.330000000000000 0.00860000000000000 0 --2 -0.220000000000000 0.00840000000000000 0 --1 -0.110000000000000 0.00830000000000000 0 -0 0 0.00820000000000000 0 -1 0.110000000000000 0.00830000000000000 0 -2 0.220000000000000 0.00840000000000000 0 -3 0.330000000000000 0.00860000000000000 0 -4 0.440000000000000 0.00890000000000000 0 -5 0.550000000000000 0.00920000000000000 0 -6 0.626800000000000 0.00980000000000000 0 -7 0.725400000000000 0.0105000000000000 0 -8 0.814300000000000 0.0114000000000000 0 -9 0.898600000000000 0.0124000000000000 0 -10 0.973900000000000 0.0135000000000000 0 -11 1.03980000000000 0.0148000000000000 0 -12 1.09060000000000 0.0162000000000000 0 -13 1.13050000000000 0.0179000000000000 0 -14 1.15800000000000 0.0196000000000000 0 -15 1.17470000000000 0.0215000000000000 0 -16 1.18230000000000 0.0236000000000000 0 -17 1.18240000000000 0.0260000000000000 0 -18 1.18140000000000 0.0285000000000000 0 -19 1.17970000000000 0.145000000000000 0 -20 1.18120000000000 0.282000000000000 0 -22 1.18930000000000 0.329000000000000 0 -25 1.22300000000000 0.405000000000000 0 -30 0.855000000000000 0.570000000000000 0 -35 0.980000000000000 0.745000000000000 0 -40 1.03500000000000 0.920000000000000 0 -45 1.05000000000000 1.07500000000000 0 -50 1.02000000000000 1.21500000000000 0 -55 0.955000000000000 1.34500000000000 0 -60 0.875000000000000 1.47000000000000 0 -65 0.760000000000000 1.57500000000000 0 -70 0.630000000000000 1.66500000000000 0 -75 0.500000000000000 1.73500000000000 0 -80 0.365000000000000 1.78000000000000 0 -85 0.230000000000000 1.80000000000000 0 -90 0.0900000000000000 1.80000000000000 0 -95 -0.0500000000000000 1.78000000000000 0 -100 -0.185000000000000 1.75000000000000 0 -105 -0.320000000000000 1.70000000000000 0 -110 -0.450000000000000 1.63500000000000 0 -115 -0.575000000000000 1.55500000000000 0 -120 -0.670000000000000 1.46500000000000 0 -125 -0.760000000000000 1.35000000000000 0 -130 -0.850000000000000 1.22500000000000 0 -135 -0.930000000000000 1.08500000000000 0 -140 -0.980000000000000 0.925000000000000 0 -145 -0.900000000000000 0.755000000000000 0 -150 -0.770000000000000 0.575000000000000 0 -155 -0.670000000000000 0.420000000000000 0 -160 -0.635000000000000 0.320000000000000 0 -165 -0.680000000000000 0.230000000000000 0 -170 -0.850000000000000 0.140000000000000 0 -175 -0.660000000000000 0.0550000000000000 0 -180 0 0.0250000000000000 0 - -Reynolds Number: 5e6 -BV Dyn. Stall Model - Positive Stall AOA (deg): 6.0 -BV Dyn. Stall Model - Negative Stall AOA (deg): -6.0 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.76 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.76 -AOA (deg) CL CD Cm25 --180 0 0.0250000000000000 0 --175 0.660000000000000 0.0550000000000000 0 --170 0.850000000000000 0.140000000000000 0 --165 0.680000000000000 0.230000000000000 0 --160 0.635000000000000 0.320000000000000 0 --155 0.670000000000000 0.420000000000000 0 --150 0.770000000000000 0.575000000000000 0 --145 0.900000000000000 0.755000000000000 0 --140 0.980000000000000 0.925000000000000 0 --135 0.930000000000000 1.08500000000000 0 --130 0.850000000000000 1.22500000000000 0 --125 0.760000000000000 1.35000000000000 0 --120 0.670000000000000 1.46500000000000 0 --115 0.575000000000000 1.55500000000000 0 --110 0.450000000000000 1.63500000000000 0 --105 0.320000000000000 1.70000000000000 0 --100 0.185000000000000 1.75000000000000 0 --95 0.0500000000000000 1.78000000000000 0 --90 -0.0900000000000000 1.80000000000000 0 --85 -0.230000000000000 1.80000000000000 0 --80 -0.365000000000000 1.78000000000000 0 --75 -0.500000000000000 1.73500000000000 0 --70 -0.630000000000000 1.66500000000000 0 --65 -0.760000000000000 1.57500000000000 0 --60 -0.875000000000000 1.47000000000000 0 --55 -0.955000000000000 1.34500000000000 0 --50 -1.02000000000000 1.21500000000000 0 --45 -1.05000000000000 1.07500000000000 0 --40 -1.03500000000000 0.920000000000000 0 --35 -0.980000000000000 0.745000000000000 0 --30 -0.855000000000000 0.570000000000000 0 --25 -1.34760000000000 0.405000000000000 0 --22 -1.31300000000000 0.329000000000000 0 --20 -1.30540000000000 0.0293000000000000 0 --19 -1.30660000000000 0.0268000000000000 0 --18 -1.30310000000000 0.0245000000000000 0 --17 -1.29770000000000 0.0224000000000000 0 --16 -1.28600000000000 0.0205000000000000 0 --15 -1.26800000000000 0.0186000000000000 0 --14 -1.24100000000000 0.0170000000000000 0 --13 -1.19790000000000 0.0156000000000000 0 --12 -1.14530000000000 0.0143000000000000 0 --11 -1.07870000000000 0.0132000000000000 0 --10 -1.00490000000000 0.0121000000000000 0 --9 -0.922200000000000 0.0112000000000000 0 --8 -0.833400000000000 0.0104000000000000 0 --7 -0.735400000000000 0.00970000000000000 0 --6 -0.660000000000000 0.00910000000000000 0 --5 -0.550000000000000 0.00860000000000000 0 --4 -0.440000000000000 0.00830000000000000 0 --3 -0.330000000000000 0.00810000000000000 0 --2 -0.220000000000000 0.00790000000000000 0 --1 -0.110000000000000 0.00780000000000000 0 -0 0 0.00780000000000000 0 -1 0.110000000000000 0.00780000000000000 0 -2 0.220000000000000 0.00790000000000000 0 -3 0.330000000000000 0.00810000000000000 0 -4 0.440000000000000 0.00830000000000000 0 -5 0.550000000000000 0.00860000000000000 0 -6 0.660000000000000 0.00910000000000000 0 -7 0.735400000000000 0.00970000000000000 0 -8 0.833400000000000 0.0104000000000000 0 -9 0.922200000000000 0.0112000000000000 0 -10 1.00490000000000 0.0121000000000000 0 -11 1.07870000000000 0.0132000000000000 0 -12 1.14530000000000 0.0143000000000000 0 -13 1.19790000000000 0.0156000000000000 0 -14 1.24100000000000 0.0170000000000000 0 -15 1.26800000000000 0.0186000000000000 0 -16 1.28600000000000 0.0205000000000000 0 -17 1.29770000000000 0.0224000000000000 0 -18 1.30310000000000 0.0245000000000000 0 -19 1.30660000000000 0.0268000000000000 0 -20 1.30540000000000 0.0293000000000000 0 -22 1.31300000000000 0.329000000000000 0 -25 1.34760000000000 0.405000000000000 0 -30 0.855000000000000 0.570000000000000 0 -35 0.980000000000000 0.745000000000000 0 -40 1.03500000000000 0.920000000000000 0 -45 1.05000000000000 1.07500000000000 0 -50 1.02000000000000 1.21500000000000 0 -55 0.955000000000000 1.34500000000000 0 -60 0.875000000000000 1.47000000000000 0 -65 0.760000000000000 1.57500000000000 0 -70 0.630000000000000 1.66500000000000 0 -75 0.500000000000000 1.73500000000000 0 -80 0.365000000000000 1.78000000000000 0 -85 0.230000000000000 1.80000000000000 0 -90 0.0900000000000000 1.80000000000000 0 -95 -0.0500000000000000 1.78000000000000 0 -100 -0.185000000000000 1.75000000000000 0 -105 -0.320000000000000 1.70000000000000 0 -110 -0.450000000000000 1.63500000000000 0 -115 -0.575000000000000 1.55500000000000 0 -120 -0.670000000000000 1.46500000000000 0 -125 -0.760000000000000 1.35000000000000 0 -130 -0.850000000000000 1.22500000000000 0 -135 -0.930000000000000 1.08500000000000 0 -140 -0.980000000000000 0.925000000000000 0 -145 -0.900000000000000 0.755000000000000 0 -150 -0.770000000000000 0.575000000000000 0 -155 -0.670000000000000 0.420000000000000 0 -160 -0.635000000000000 0.320000000000000 0 -165 -0.680000000000000 0.230000000000000 0 -170 -0.850000000000000 0.140000000000000 0 -175 -0.660000000000000 0.0550000000000000 0 -180 0 0.0250000000000000 0 - -Reynolds Number: 8e6 -BV Dyn. Stall Model - Positive Stall AOA (deg): 10.0 -BV Dyn. Stall Model - Negative Stall AOA (deg): -10.0 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.131 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.82 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.82 -AOA (deg) CL CD Cm25 --180 0 0.0250000000000000 0 --175 0.660000000000000 0.0550000000000000 0 --170 0.850000000000000 0.140000000000000 0 --165 0.680000000000000 0.230000000000000 0 --160 0.635000000000000 0.320000000000000 0 --155 0.670000000000000 0.420000000000000 0 --150 0.770000000000000 0.575000000000000 0 --145 0.900000000000000 0.755000000000000 0 --140 0.980000000000000 0.925000000000000 0 --135 0.930000000000000 1.08500000000000 0 --130 0.850000000000000 1.22500000000000 0 --125 0.760000000000000 1.35000000000000 0 --120 0.670000000000000 1.46500000000000 0 --115 0.575000000000000 1.55500000000000 0 --110 0.450000000000000 1.63500000000000 0 --105 0.320000000000000 1.70000000000000 0 --100 0.185000000000000 1.75000000000000 0 --95 0.0500000000000000 1.78000000000000 0 --90 -0.0900000000000000 1.80000000000000 0 --85 -0.230000000000000 1.80000000000000 0 --80 -0.365000000000000 1.78000000000000 0 --75 -0.500000000000000 1.73500000000000 0 --70 -0.630000000000000 1.66500000000000 0 --65 -0.760000000000000 1.57500000000000 0 --60 -0.875000000000000 1.47000000000000 0 --55 -0.955000000000000 1.34500000000000 0 --50 -1.02000000000000 1.21500000000000 0 --45 -1.05000000000000 1.07500000000000 0 --40 -1.03500000000000 0.920000000000000 0 --35 -0.980000000000000 0.745000000000000 0 --30 -0.855000000000000 0.570000000000000 0 --22 -1.45100000000000 0.329000000000000 0 --20 -1.43500000000000 0.282000000000000 0 --18 -1.41500000000000 0.135000000000000 0 --16 -1.37700000000000 0.0199000000000000 0 --15 -1.34400000000000 0.0184000000000000 0 --14 -1.30100000000000 0.0170000000000000 0 --13 -1.24800000000000 0.0157000000000000 0 --12 -1.18200000000000 0.0145000000000000 0 --11 -1.10800000000000 0.0134000000000000 0 --10 -1.02400000000000 0.0124000000000000 0 --9 -0.935000000000000 0.0115000000000000 0 --8 -0.841000000000000 0.0107000000000000 0 --7 -0.744000000000000 0.00990000000000000 0 --6 -0.639000000000000 0.00930000000000000 0 --5 -0.533000000000000 0.00880000000000000 0 --4 -0.426000000000000 0.00840000000000000 0 --3 -0.320000000000000 0.00800000000000000 0 --2 -0.213000000000000 0.00780000000000000 0 --1 -0.107000000000000 0.00770000000000000 0 -0 0 0.00760000000000000 0 -1 0.107000000000000 0.00770000000000000 0 -2 0.213000000000000 0.00780000000000000 0 -3 0.320000000000000 0.00800000000000000 0 -4 0.426000000000000 0.00840000000000000 0 -5 0.533000000000000 0.00880000000000000 0 -6 0.639000000000000 0.00930000000000000 0 -7 0.744000000000000 0.00990000000000000 0 -8 0.841000000000000 0.0107000000000000 0 -9 0.935000000000000 0.0115000000000000 0 -10 1.02400000000000 0.0124000000000000 0 -11 1.10800000000000 0.0134000000000000 0 -12 1.18200000000000 0.0145000000000000 0 -13 1.24800000000000 0.0157000000000000 0 -14 1.30100000000000 0.0170000000000000 0 -15 1.34400000000000 0.0184000000000000 0 -16 1.37700000000000 0.0199000000000000 0 -18 1.41500000000000 0.135000000000000 0 -20 1.43500000000000 0.282000000000000 0 -22 1.45100000000000 0.329000000000000 0 -30 0.855000000000000 0.570000000000000 0 -35 0.980000000000000 0.745000000000000 0 -40 1.03500000000000 0.920000000000000 0 -45 1.05000000000000 1.07500000000000 0 -50 1.02000000000000 1.21500000000000 0 -55 0.955000000000000 1.34500000000000 0 -60 0.875000000000000 1.47000000000000 0 -65 0.760000000000000 1.57500000000000 0 -70 0.630000000000000 1.66500000000000 0 -75 0.500000000000000 1.73500000000000 0 -80 0.365000000000000 1.78000000000000 0 -85 0.230000000000000 1.80000000000000 0 -90 0.0900000000000000 1.80000000000000 0 -95 -0.0500000000000000 1.78000000000000 0 -100 -0.185000000000000 1.75000000000000 0 -105 -0.320000000000000 1.70000000000000 0 -110 -0.450000000000000 1.63500000000000 0 -115 -0.575000000000000 1.55500000000000 0 -120 -0.670000000000000 1.46500000000000 0 -125 -0.760000000000000 1.35000000000000 0 -130 -0.850000000000000 1.22500000000000 0 -135 -0.930000000000000 1.08500000000000 0 -140 -0.980000000000000 0.925000000000000 0 -145 -0.900000000000000 0.755000000000000 0 -150 -0.770000000000000 0.575000000000000 0 -155 -0.670000000000000 0.420000000000000 0 -160 -0.635000000000000 0.320000000000000 0 -165 -0.680000000000000 0.230000000000000 0 -170 -0.850000000000000 0.140000000000000 0 -175 -0.660000000000000 0.0550000000000000 0 -180 0 0.0250000000000000 0 diff --git a/examples/helical_riverine/helical_riverine_driver.jl b/examples/helical_riverine/helical_riverine_driver.jl index 572a2c1a..76b477c2 100644 --- a/examples/helical_riverine/helical_riverine_driver.jl +++ b/examples/helical_riverine/helical_riverine_driver.jl @@ -48,19 +48,19 @@ nbelem = 60 ncelem = 10 nselem = 5 ifw = false -AModel = "DMS" +AModel = "AD" windINPfilename = "$path/300mx300m12msETM_Coarse.bts" ifw_libfile = nothing#"$path/../../openfast/build/modules/inflowwind/libifw_c_binding" Blade_Height = 41.9 Blade_Radius = 6.0 -numTS = 100 +numTS = 10 delta_t = 0.05 NuMad_geom_xlscsv_file_twr = "$path/TowerGeom.csv" NuMad_mat_xlscsv_file_twr = "$path/TowerMaterials.csv" -NuMad_geom_xlscsv_file_bld = "$path/GeomBlades_AD.csv" -NuMad_mat_xlscsv_file_bld = "$path/NuMAD_SNL34mMaterials.csv" +NuMad_geom_xlscsv_file_bld = "$path/GeomBlades.csv" +NuMad_mat_xlscsv_file_bld = "$path/Materials34m.csv" NuMad_geom_xlscsv_file_strut = "$path/GeomStruts.csv" -NuMad_mat_xlscsv_file_strut = "$path/NuMAD_SNL34mMaterials.csv" +NuMad_mat_xlscsv_file_strut = "$path/Materials34m.csv" adi_lib = nothing#"$path/../../../openfast/build/modules/aerodyn/libaerodyn_inflow_c_binding" adi_rootname = "$path/helical" @@ -74,23 +74,8 @@ Omegaocp = [34.0; 34.0; 34.0]./60 #control inputs tocp_Vinf = [0.0;10.0; 1e6] Vinfocp = [10.0;10.0;10.0] -# windio -controlpts = [3.6479257474344826, 6.226656883619295, 9.082267631309085, 11.449336766507562, 13.310226748873827, 14.781369210504563, 15.8101544043681, 16.566733104331984, 17.011239869982738, 17.167841319391137, 17.04306679619916, 16.631562597633675, 15.923729603782338, 14.932185789551408, 13.62712239754136, 12.075292152969496, 10.252043906945818, 8.124505683235517, 5.678738418596312, 2.8959968657512207] - -# z_shape = collect(LinRange(0,41.9,length(x_shape))) -z_shape1 = collect(LinRange(0,41.9,length(controlpts)+2)) -x_shape1 = [0.0;controlpts;0.0] -z_shape = collect(LinRange(0,41.9,60)) -x_shape = FLOWMath.akima(z_shape1,x_shape1,z_shape)#[0.0,1.7760245854312287, 5.597183088188207, 8.807794161662574, 11.329376903432605, 13.359580331518579, 14.833606099357858, 15.945156349709, 16.679839160110422, 17.06449826588358, 17.10416552269884, 16.760632435904647, 16.05982913536134, 15.02659565585254, 13.660910465851046, 11.913532434360155, 9.832615229216344, 7.421713825584581, 4.447602800040282, 0.0] -toweroffset = 4.3953443986241725 -SNL34_unit_xz = [x_shape;;z_shape] -SNL34x = SNL34_unit_xz[:,1]./maximum(SNL34_unit_xz[:,1]) -SNL34z = SNL34_unit_xz[:,2]./maximum(SNL34_unit_xz[:,2]) -SNL34Z = SNL34z.*Blade_Height #windio -SNL34X = SNL34x.*Blade_Radius #windio - -shapeZ = SNL34Z#collect(LinRange(0,H,Nslices+1)) -helix_angle = pi/4 +shapeZ = collect(LinRange(0,Blade_Height,Nslices+1)) +helix_angle = -pi/4 shapeX = cos.(shapeZ/maximum(shapeZ)*helix_angle).*Blade_Radius#SNL34X#R.*(1.0.-4.0.*(shapeZ/H.-.5).^2)#shapeX_spline(shapeZ) ones(length(shapeZ)).*Blade_Radius# shapeY = sin.(shapeZ/maximum(shapeZ)*helix_angle).*Blade_Radius # zeros(length(shapeX))# @@ -102,8 +87,6 @@ mass_breakout_blds,mass_breakout_twr,system, assembly, sections,AD15bldNdIdxRng, rho, #windio Nslices, #modeling options ntheta, #modeling options - RPM, #remove - Vinf, #remove eta, #windio B = Nbld, #windio H = Blade_Height, #windio @@ -125,14 +108,14 @@ mass_breakout_blds,mass_breakout_twr,system, assembly, sections,AD15bldNdIdxRng, NuMad_mat_xlscsv_file_bld,#windio NuMad_geom_xlscsv_file_strut,#windio NuMad_mat_xlscsv_file_strut,#windio - Ht=towerHeight, + Htwr_base=towerHeight, ntelem, nbelem, ncelem, nselem, joint_type = 0, - strut_mountpointbot = 0.03, - strut_mountpointtop = 0.03, + strut_twr_mountpoint = [0.1,0.5,0.9], + strut_bld_mountpoint = [0.05,0.5,0.95], AModel, #AD, DMS, AC DSModel="BV", RPI=true, @@ -281,7 +264,7 @@ for it = 1:length(t) end azi=aziHist#./aziHist*1e-6 -saveName = "$path/vtk/RM2" +saveName = "$path/vtk/helical" OWENS.OWENSFEA_VTK(saveName,t,uHist,system,assembly,sections;scaling=1,azi,userPointNames,userPointData) # Open Paraview, open animation pane, adjust as desired, export animation (which exports frames) diff --git a/src/OWENS.jl b/src/OWENS.jl index 9384bbaa..f39da28b 100644 --- a/src/OWENS.jl +++ b/src/OWENS.jl @@ -72,5 +72,6 @@ include("./meshing_utilities.jl") include("./gxbeam_conversion.jl") include("./SetupTurbine.jl") include("./topRunDLC.jl") +include("./windio.jl") end diff --git a/src/PostProcessing.jl b/src/PostProcessing.jl index 446e03d9..4e6daf35 100644 --- a/src/PostProcessing.jl +++ b/src/PostProcessing.jl @@ -508,7 +508,7 @@ function printSF(verbosity,SF_ult,SF_buck,LE_idx,TE_idx,SparCap_idx,ForePanel_id minbuck_sf,minbuck_sfidx = findmin(SF_buck) if verbosity>2 println("\nWorst buckling safety factor $(minbuck_sf)") - println("At time $(minbuck_sfidx[1]*0.05)s at composite station $(minbuck_sfidx2) of $(lencomposites_span) at lam $(minbuck_sfidx[3]) of $(length(lam_used[minbuck_sfidx2,:]))") + println("At time $(minbuck_sfidx[1]*0.05)s at composite station $(minbuck_sfidx[2]) of $(lencomposites_span) at lam $(minbuck_sfidx[3]) of $(length(lam_used[minbuck_sfidx[2],:]))") end if verbosity>3 println("Buckling") diff --git a/src/SetupTurbine.jl b/src/SetupTurbine.jl index 8707adca..647bdcca 100644 --- a/src/SetupTurbine.jl +++ b/src/SetupTurbine.jl @@ -1,3 +1,6 @@ +# * `strut_twr_mountpoint::float` = [0.01,0.5,0.9], # factor of blade height where the bottom strut attaches on the tower # This puts struts at top and bottom, as a fraction of the blade position +# * `strut_bld_mountpoint::float` = [0.01,0.5,0.9], # factor of blade height where the bottom strut attaches on the blade # This puts struts at bottom 0, mid 0.5, and top 1.0 as a fraction of the blade position +# NuMad_geom_xlscsv_file_strut = nothing, or sting for the filename, or array of strings matching length of Nstruts (length(strut_twr_mountpoint)) function setupOWENS(OWENSAero,path; rho = 1.225, mu = 1.7894e-5, @@ -35,11 +38,10 @@ function setupOWENS(OWENSAero,path; stack_layers_scale = [1.0,1.0], chord_scale = [1.0,1.0], thickness_scale = [1.0,1.0], - Ht=2.0, - strut_mountpointbot = 0.11, - strut_mountpointtop = 0.11, - strut_mountpointbottwr = nothing, - strut_mountpointtoptwr = nothing, + Htwr_base = 2.0, + Htwr_blds = H, + strut_twr_mountpoint = [0.25,0.75], + strut_bld_mountpoint = [0.25,0.75], joint_type = 2, c_mount_ratio = 0.05, angularOffset = -pi/2, @@ -48,14 +50,6 @@ function setupOWENS(OWENSAero,path; RPI=true, cables_connected_to_blade_base = true, meshtype = "Darrieus") #Darrieus, H-VAWT, ARCUS - - if isnothing(strut_mountpointbottwr) - strut_mountpointbottwr = strut_mountpointbot - end - - if isnothing(strut_mountpointtoptwr) - strut_mountpointtoptwr = strut_mountpointtop - end if AModel=="AD" AD15On = true @@ -66,7 +60,7 @@ function setupOWENS(OWENSAero,path; # Here is where we take the inputs from setupOWENS and break out what is going on behind the function. # We do some intermediate calculations on the blade shape and angles - Nstrutperbld = 2 #TODO: generalize and propogate + Nstrutperbld = length(strut_twr_mountpoint) Nbld = B H = maximum(shapeZ) #m, @@ -84,8 +78,8 @@ function setupOWENS(OWENSAero,path; ### Set up mesh ######################################### if meshtype == "ARCUS" #TODO, for all of these propogate the AeroDyn additional output requirements - mymesh,myort,myjoint = OWENS.create_arcus_mesh(;Ht, - Hb = H, #blade height + mymesh,myort,myjoint = OWENS.create_arcus_mesh(;Htwr_base, + Hbld = H, #blade height R, # m bade radius nblade = Nbld, ntelem, #tower elements @@ -105,18 +99,17 @@ function setupOWENS(OWENSAero,path; connectBldTips2Twr = false end - mymesh, myort, myjoint, AD15bldNdIdxRng, AD15bldElIdxRng = OWENS.create_mesh_struts(;Ht, - Hb = H, #blade height + mymesh, myort, myjoint, AD15bldNdIdxRng, AD15bldElIdxRng = OWENS.create_mesh_struts(;Htwr_base, + Htwr_blds, + Hbld = H, #blade height R, # m bade radius AD15hubR, #TODO: hook up with AD15 file generation nblade = Nbld, ntelem, #tower elements nbelem, #blade elements nselem, - strut_twr_mountpointbot = strut_mountpointbottwr, # This puts struts at top and bottom - strut_twr_mountpointtop = strut_mountpointtoptwr, # This puts struts at top and bottom - strut_bld_mountpointbot = strut_mountpointbot, # This puts struts at top and bottom - strut_bld_mountpointtop = strut_mountpointtop, # This puts struts at top and bottom + strut_twr_mountpoint, + strut_bld_mountpoint, bshapex = shapeX, #Blade shape, magnitude is irrelevant, scaled based on height and radius above bshapez = shapeZ, bshapey = shapeY, # but magnitude for this is relevant @@ -127,7 +120,7 @@ function setupOWENS(OWENSAero,path; else #TODO unify with HAWT error("please choose a valid mesh type (Darrieus, H-VAWT, ARCUS)") end - + nTwrElem = Int(mymesh.meshSeg[1]) if contains(NuMad_mat_xlscsv_file_bld,"34m") #TODO: this is really odd, nTwrElem = Int(mymesh.meshSeg[1])+1 @@ -264,68 +257,83 @@ function setupOWENS(OWENSAero,path; nothing # Similarly for the struts, we do what was done for the blades - if !isnothing(NuMad_geom_xlscsv_file_strut) - numadIn_strut = OWENS.readNuMadGeomCSV(NuMad_geom_xlscsv_file_strut) - else - n_web = 1 - n_stack = 7 - n_segments = 12 - span = [0.0, 6.607, 13.215, 19.822, 26.43, 33.037, 39.645, 46.252, 52.859, 59.467, 66.074, 72.682, 79.289, 85.896, 92.504, 99.111, 105.719, 112.326, 118.934, 125.541, 132.148] - airfoil = ["circular", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021"] - te_type = ["round", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp"] - twist_d = [0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0] - chord = [10.0, 10.0, 9.0, 8.0, 8.0, 7.0, 7.0, 6.0, 6.0, 6.0, 5.0, 5.0, 5.0, 5.0, 5.0, 5.0, 5.0, 5.0, 5.0, 5.0, 5.0] - xoffset = [0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3] - aerocenter = [0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2] - stack_mat_types = [8, 2, 4, 8, 8, 8, 4] - if isnothing(stack_layers_strut) - stack_layers = [30.0 2.0 15.0 25.0 25.0 2.0 13.0; 15.0 2.0 10.0 13.0 11.0 2.0 11.0; 10.0 1.0 8.0 10.0 10.0 2.0 10.0; 8.0 1.0 6.0 9.0 10.0 1.0 9.0; 7.0 1.0 5.0 8.0 9.0 1.0 7.0; 6.0 1.0 4.0 8.0 9.0 1.0 6.0; 6.0 1.0 4.0 8.0 8.0 1.0 5.0; 6.0 1.0 4.0 7.0 7.0 1.0 5.0; 7.0 1.0 3.0 6.0 6.0 1.0 5.0; 8.0 1.0 3.0 6.0 6.0 1.0 5.0; 8.0 1.0 3.0 6.0 6.0 1.0 5.0; 7.0 1.0 3.0 6.0 6.0 1.0 5.0; 7.0 1.0 3.0 6.0 6.0 2.0 5.0; 7.0 1.0 3.0 6.0 6.0 2.0 5.0; 7.0 1.0 3.0 7.0 8.0 3.0 5.0; 7.0 2.0 3.0 9.0 12.0 3.0 6.0; 10.0 3.0 4.0 11.0 15.0 3.0 6.0; 12.0 3.0 4.0 13.0 15.0 3.0 6.0; 12.0 3.0 4.0 15.0 15.0 3.0 6.0; 12.0 3.0 4.0 15.0 15.0 3.0 6.0; 10.0 1.0 4.0 10.0 12.0 1.0 5.0] + numadIn_strut = Array{NuMad, 1}(undef, Nstrutperbld) + strut_precompoutput = Array{Array{OWENSPreComp.Output, 1},1}(undef, Nstrutperbld) + strut_precompinput = Array{Array{OWENSPreComp.Input, 1},1}(undef, Nstrutperbld) + lam_U_strut = Array{Array{Composites.Laminate, 2}}(undef, Nstrutperbld) + lam_L_strut = Array{Array{Composites.Laminate, 2}}(undef, Nstrutperbld) + lam_W_strut = Array{Array{Composites.Laminate, 2}}(undef, Nstrutperbld) + sectionPropsArray_strut = Array{Array{OWENSFEA.SectionPropsArray, 1}}(undef, Nstrutperbld) + stiff_strut = Array{Array{Array{Float64,2}, 1},1}(undef, Nstrutperbld) + mass_strut = Array{Array{Array{Float64,2}, 1},1}(undef, Nstrutperbld) + for istrut = 1:Nstrutperbld + if !isnothing(NuMad_geom_xlscsv_file_strut) + if typeof(NuMad_geom_xlscsv_file_strut)==String + numadIn_strut[istrut] = OWENS.readNuMadGeomCSV(NuMad_geom_xlscsv_file_strut) + else + numadIn_strut[istrut] = OWENS.readNuMadGeomCSV(NuMad_geom_xlscsv_file_strut[istrut]) + end else - stack_layers = stack_layers_strut + n_web = 1 + n_stack = 7 + n_segments = 12 + span = [0.0, 6.607, 13.215, 19.822, 26.43, 33.037, 39.645, 46.252, 52.859, 59.467, 66.074, 72.682, 79.289, 85.896, 92.504, 99.111, 105.719, 112.326, 118.934, 125.541, 132.148] + airfoil = ["circular", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021"] + te_type = ["round", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp"] + twist_d = [0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0] + chord = [10.0, 10.0, 9.0, 8.0, 8.0, 7.0, 7.0, 6.0, 6.0, 6.0, 5.0, 5.0, 5.0, 5.0, 5.0, 5.0, 5.0, 5.0, 5.0, 5.0, 5.0] + xoffset = [0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3] + aerocenter = [0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2] + stack_mat_types = [8, 2, 4, 8, 8, 8, 4] + if isnothing(stack_layers_strut) + stack_layers = [30.0 2.0 15.0 25.0 25.0 2.0 13.0; 15.0 2.0 10.0 13.0 11.0 2.0 11.0; 10.0 1.0 8.0 10.0 10.0 2.0 10.0; 8.0 1.0 6.0 9.0 10.0 1.0 9.0; 7.0 1.0 5.0 8.0 9.0 1.0 7.0; 6.0 1.0 4.0 8.0 9.0 1.0 6.0; 6.0 1.0 4.0 8.0 8.0 1.0 5.0; 6.0 1.0 4.0 7.0 7.0 1.0 5.0; 7.0 1.0 3.0 6.0 6.0 1.0 5.0; 8.0 1.0 3.0 6.0 6.0 1.0 5.0; 8.0 1.0 3.0 6.0 6.0 1.0 5.0; 7.0 1.0 3.0 6.0 6.0 1.0 5.0; 7.0 1.0 3.0 6.0 6.0 2.0 5.0; 7.0 1.0 3.0 6.0 6.0 2.0 5.0; 7.0 1.0 3.0 7.0 8.0 3.0 5.0; 7.0 2.0 3.0 9.0 12.0 3.0 6.0; 10.0 3.0 4.0 11.0 15.0 3.0 6.0; 12.0 3.0 4.0 13.0 15.0 3.0 6.0; 12.0 3.0 4.0 15.0 15.0 3.0 6.0; 12.0 3.0 4.0 15.0 15.0 3.0 6.0; 10.0 1.0 4.0 10.0 12.0 1.0 5.0] + else + stack_layers = stack_layers_strut + end + segments = [-1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0] + DPtypes = ["" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""] + skin_seq = [Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2])] + web_seq = [Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]);;] + web_dp = [Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]);;] + + numadIn_strut[istrut] = NuMad(n_web,n_stack,n_segments,span,airfoil,te_type,twist_d,chord,xoffset,aerocenter,stack_mat_types,stack_layers,segments,DPtypes,skin_seq,web_seq,web_dp) end - segments = [-1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0] - DPtypes = ["" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""] - skin_seq = [Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2])] - web_seq = [Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]);;] - web_dp = [Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]);;] + for icol = 1:length(numadIn_strut[istrut].stack_layers[1,:]) + numadIn_strut[istrut].stack_layers[:,icol] .*= LinRange(stack_layers_scale[1],stack_layers_scale[2],length(numadIn_strut[istrut].chord)) + end + numadIn_strut[istrut].chord .*= LinRange(chord_scale[1],chord_scale[2],length(numadIn_strut[istrut].chord)) - numadIn_strut = NuMad(n_web,n_stack,n_segments,span,airfoil,te_type,twist_d,chord,xoffset,aerocenter,stack_mat_types,stack_layers,segments,DPtypes,skin_seq,web_seq,web_dp) - end - for icol = 1:length(numadIn_strut.stack_layers[1,:]) - numadIn_strut.stack_layers[:,icol] .*= LinRange(stack_layers_scale[1],stack_layers_scale[2],length(numadIn_strut.chord)) - end - numadIn_strut.chord .*= LinRange(chord_scale[1],chord_scale[2],length(numadIn_strut.chord)) + for (i,airfoil) in enumerate(numadIn_strut[istrut].airfoil) + numadIn_strut[istrut].airfoil[i] = "$path/airfoils/$airfoil" + end - for (i,airfoil) in enumerate(numadIn_strut.airfoil) - numadIn_strut.airfoil[i] = "$path/airfoils/$airfoil" - end + if !isnothing(NuMad_mat_xlscsv_file_strut) + plyprops_strut = OWENS.readNuMadMaterialsCSV(NuMad_mat_xlscsv_file_strut) + else + names = ["CLA_5500", "CBX_2400", "ETLX_2400", "Airex_C70_55", "EBX_2400_x10", "ETLX_2400_x10", "Airex_C70_55_x10", "CFP-baseline"] + plies = [Composites.Material{Float64}(9.824e10, 5.102e9, 4.274e9, 0.3, 1540.0, 8.75634139e8, 5.92949102e8, 1.0e8, 1.0e8, 1.0e8, 0.00066), Composites.Material{Float64}(1.4931e10, 1.4931e10, 2.389e10, 0.3, 1530.0, 4.55053962e8, 4.55053962e8, 1.0e8, 1.0e8, 1.0e8, 0.0008100000000000001), Composites.Material{Float64}(2.0333e10, 9.305e9, 4.756e9, 0.3, 1900.0, 5.30896289e8, 5.30896289e8, 1.0e8, 1.0e8, 1.0e8, 0.00066), Composites.Material{Float64}(4.5e7, 4.5e7, 2.2e7, 0.2, 59.0, 1.0e8, 1.0e8, 1.0e8, 1.0e8, 1.0e8, 0.001), Composites.Material{Float64}(9.824e11, 5.102e10, 4.274e10, 0.3, 15300.0, 4.55053962e9, 4.55053962e9, 1.0e8, 1.0e8, 1.0e8, 7.000000000000001e-5), Composites.Material{Float64}(1.4931e11, 1.4931e11, 2.389e11, 0.3, 19000.0, 5.30896289e9, 5.30896289e9, 1.0e8, 1.0e8, 1.0e8, 8.0e-5), Composites.Material{Float64}(2.03335e11, 9.3051e10, 4.756e10, 0.2, 590.0, 1.0e8, 1.0e8, 1.0e8, 1.0e8, 1.0e8, 7.000000000000001e-5), Composites.Material{Float64}(1.576e11, 9.1e9, 3.3e9, 0.263, 1600.0, 2.236e9, 1.528e9, 1.0e8, 1.0e8, 1.0e8, 0.00066)] + plyprops_strut = OWENS.plyproperties(names,plies) + end - if !isnothing(NuMad_mat_xlscsv_file_strut) - plyprops_strut = OWENS.readNuMadMaterialsCSV(NuMad_mat_xlscsv_file_strut) - else - names = ["CLA_5500", "CBX_2400", "ETLX_2400", "Airex_C70_55", "EBX_2400_x10", "ETLX_2400_x10", "Airex_C70_55_x10", "CFP-baseline"] - plies = [Composites.Material{Float64}(9.824e10, 5.102e9, 4.274e9, 0.3, 1540.0, 8.75634139e8, 5.92949102e8, 1.0e8, 1.0e8, 1.0e8, 0.00066), Composites.Material{Float64}(1.4931e10, 1.4931e10, 2.389e10, 0.3, 1530.0, 4.55053962e8, 4.55053962e8, 1.0e8, 1.0e8, 1.0e8, 0.0008100000000000001), Composites.Material{Float64}(2.0333e10, 9.305e9, 4.756e9, 0.3, 1900.0, 5.30896289e8, 5.30896289e8, 1.0e8, 1.0e8, 1.0e8, 0.00066), Composites.Material{Float64}(4.5e7, 4.5e7, 2.2e7, 0.2, 59.0, 1.0e8, 1.0e8, 1.0e8, 1.0e8, 1.0e8, 0.001), Composites.Material{Float64}(9.824e11, 5.102e10, 4.274e10, 0.3, 15300.0, 4.55053962e9, 4.55053962e9, 1.0e8, 1.0e8, 1.0e8, 7.000000000000001e-5), Composites.Material{Float64}(1.4931e11, 1.4931e11, 2.389e11, 0.3, 19000.0, 5.30896289e9, 5.30896289e9, 1.0e8, 1.0e8, 1.0e8, 8.0e-5), Composites.Material{Float64}(2.03335e11, 9.3051e10, 4.756e10, 0.2, 590.0, 1.0e8, 1.0e8, 1.0e8, 1.0e8, 1.0e8, 7.000000000000001e-5), Composites.Material{Float64}(1.576e11, 9.1e9, 3.3e9, 0.263, 1600.0, 2.236e9, 1.528e9, 1.0e8, 1.0e8, 1.0e8, 0.00066)] - plyprops_strut = OWENS.plyproperties(names,plies) - end + #TODO: not straight struts + spanpos = LinRange(0,1,nselem+1)#[0.0;cumsum(sqrt.(diff(mymesh.x[strut1start:strut1end]).^2 .+ diff(mymesh.z[strut1start:strut1end]).^2))] - #TODO: not straight struts - spanpos = LinRange(0,1,nselem+1)#[0.0;cumsum(sqrt.(diff(mymesh.x[strut1start:strut1end]).^2 .+ diff(mymesh.z[strut1start:strut1end]).^2))] + if length(thickness_scale)==2 + yscale = collect(LinRange(thickness_scale[1],thickness_scale[2],length(numadIn_strut[istrut].span))) + elseif length(thickness_scale)==length(numadIn_strut[istrut].span) + yscale = thickness_scale + end - if length(thickness_scale)==2 - yscale = collect(LinRange(thickness_scale[1],thickness_scale[2],length(numadIn_strut.span))) - elseif length(thickness_scale)==length(numadIn_strut.span) - yscale = thickness_scale + strut_precompoutput[istrut],strut_precompinput[istrut],lam_U_strut[istrut],lam_L_strut[istrut],lam_W_strut[istrut] = OWENS.getOWENSPreCompOutput(numadIn_strut[istrut];yscale,plyprops = plyprops_strut) + sectionPropsArray_strut[istrut] = OWENS.getSectPropsFromOWENSPreComp(spanpos,numadIn_strut[istrut],strut_precompoutput[istrut];precompinputs=strut_precompinput[istrut]) + stiff_strut[istrut], mass_strut[istrut] = OWENS.getSectPropsFromOWENSPreComp(spanpos,numadIn_strut[istrut],strut_precompoutput[istrut];GX=true) end - strut_precompoutput,strut_precompinput,lam_U_strut,lam_L_strut,lam_W_strut = OWENS.getOWENSPreCompOutput(numadIn_strut;yscale,plyprops = plyprops_strut) - sectionPropsArray_strut = OWENS.getSectPropsFromOWENSPreComp(spanpos,numadIn_strut,strut_precompoutput;precompinputs=strut_precompinput) - stiff_strut, mass_strut = OWENS.getSectPropsFromOWENSPreComp(spanpos,numadIn_strut,strut_precompoutput;GX=true) - nothing # Here we combine the section properties into an array matching the mesh elements bldssecprops = collect(Iterators.flatten(fill(sectionPropsArray_bld, Nbld))) - strutssecprops = collect(Iterators.flatten(fill(sectionPropsArray_strut, Nstrutperbld*Nbld))) + # strutssecprops = collect(Iterators.flatten(fill(sectionPropsArray_strut, Nstrutperbld*Nbld))) if meshtype == "ARCUS" cable_secprop = sectionPropsArray_twr[end] @@ -341,16 +349,21 @@ function setupOWENS(OWENSAero,path; mass_cables = fill(mass_twr[end],Nremain) mass_array = [mass_twr; mass_blds; mass_cables] else - sectionPropsArray = [sectionPropsArray_twr; bldssecprops; strutssecprops]#;sectionPropsArray_str;sectionPropsArray_str;sectionPropsArray_str;sectionPropsArray_str] - - # GXBeam sectional properties + sectionPropsArray = [sectionPropsArray_twr; bldssecprops]#; strutssecprops]#;sectionPropsArray_str;sectionPropsArray_str;sectionPropsArray_str;sectionPropsArray_str] + stiff_blds = collect(Iterators.flatten(fill(stiff_bld, Nbld))) - stiff_struts = collect(Iterators.flatten(fill(stiff_strut, Nstrutperbld*Nbld))) - stiff_array = [stiff_twr; stiff_blds; stiff_struts] + stiff_array = [stiff_twr; stiff_blds]#; stiff_struts] mass_blds = collect(Iterators.flatten(fill(mass_bld, Nbld))) - mass_struts = collect(Iterators.flatten(fill(mass_strut, Nstrutperbld*Nbld))) - mass_array = [mass_twr; mass_blds; mass_struts] + mass_array = [mass_twr; mass_blds]#; mass_struts] + + for istrut = 1:Nstrutperbld + for ibld = 1:Nbld + sectionPropsArray = [sectionPropsArray; sectionPropsArray_strut[istrut]] + stiff_array = [stiff_array;stiff_strut[istrut]] + mass_array = [mass_array;mass_strut[istrut]] + end + end end rotationalEffects = ones(mymesh.numEl) #TODO: non rotating tower, or rotating blades @@ -410,43 +423,64 @@ function setupOWENS(OWENSAero,path; # Here we create AeroDyn the files, first by specifying the names, then by creating the files, TODO: hook up the direct sectionPropsArray_str # Then by initializing AeroDyn and grabbing the backend functionality with a function handle if AD15On - ad_input_file="$path/ADInputFile_SingleTurbine2.dat" - ifw_input_file="$path/IW2.dat" - blade_filename="$path/blade2.dat" - lower_strut_filename="$path/lower_arm2.dat" - upper_strut_filename="$path/upper_arm2.dat" + ad_input_file = "$path/ADInputFile_SingleTurbine2.dat" + ifw_input_file = "$path/IW2.dat" OLAF_filename = "$path/OLAF2.dat" NumADBldNds = NumADStrutNds = 10 bldchord_spl = FLOWMath.akima(numadIn_bld.span./maximum(numadIn_bld.span), numadIn_bld.chord,LinRange(0,1,NumADBldNds)) - # Discretely assign the airfoils #TODO: separate out struts - airfoil_filenames = fill("nothing",NumADBldNds) + # Discretely assign the blade airfoils based on the next closest neighbor + bld_airfoil_filenames = fill("nothing",NumADBldNds) #TODO: cable drag? for (ispan_numad,span_numad) in enumerate(numadIn_bld.span./maximum(numadIn_bld.span)) for (ispan,span_slices) in enumerate(collect(LinRange(0,1,NumADBldNds))) - if airfoil_filenames[ispan]=="nothing" && span_slices<=span_numad - airfoil_filenames[ispan] = "$(numadIn_bld.airfoil[ispan_numad]).dat" + if bld_airfoil_filenames[ispan]=="nothing" && span_slices<=span_numad + bld_airfoil_filenames[ispan] = "$(numadIn_bld.airfoil[ispan_numad]).dat" end end end if meshtype == "ARCUS" - blade_filenames = [blade_filename for i=1:Nbld] + blade_filenames = ["$path/blade$i.dat" for i=1:Nbld] blade_chords = [bldchord_spl for i=1:Nbld] blade_Nnodes = [NumADBldNds for i=1:Nbld] + airfoil_filenames = [bld_airfoil_filenames for i=1:Nbld] + else - blade_filenames = [[blade_filename for i=1:Nbld];[lower_strut_filename for i=1:Nbld];[upper_strut_filename for i=1:Nbld]] - strutchord_spl = FLOWMath.akima(numadIn_strut.span./maximum(numadIn_strut.span), numadIn_strut.chord,LinRange(0,1,NumADStrutNds)) - blade_chords = [[bldchord_spl for i=1:Nbld];[strutchord_spl for i=1:Nbld];[strutchord_spl for i=1:Nbld]] - blade_Nnodes = [[NumADBldNds for i=1:Nbld];[NumADStrutNds for i=1:Nbld];[NumADStrutNds for i=1:Nbld]] + blade_filenames = ["$path/blade$i.dat" for i=1:Nbld] + blade_chords = [bldchord_spl for i=1:Nbld] + blade_Nnodes = [NumADBldNds for i=1:Nbld] + airfoil_filenames = collect(Iterators.flatten([bld_airfoil_filenames for i=1:Nbld])) + + for istrut = 1:Nstrutperbld + strutchord_spl = FLOWMath.akima(numadIn_strut[istrut].span./maximum(numadIn_strut[istrut].span), numadIn_strut[istrut].chord,LinRange(0,1,NumADStrutNds)) + for ibld = 1:Nbld + blade_filenames = [blade_filenames;"$path/strut$(istrut)_bld$ibld.dat"] + blade_chords = [blade_chords;[strutchord_spl]] + blade_Nnodes = [blade_Nnodes;NumADStrutNds] + + # Discretely assign the strut airfoils based on the next closest neighbor + strut_airfoil_filenames = fill("nothing",NumADStrutNds) + for (ispan_numad,span_numad) in enumerate(numadIn_strut[istrut].span./maximum(numadIn_strut[istrut].span)) + for (ispan,span_slices) in enumerate(collect(LinRange(0,1,NumADBldNds))) + if strut_airfoil_filenames[ispan]=="nothing" && span_slices<=span_numad + strut_airfoil_filenames[ispan] = "$(numadIn_strut[istrut].airfoil[ispan_numad]).dat" + end + end + end + + airfoil_filenames = [airfoil_filenames; strut_airfoil_filenames] + + end + end end OWENSOpenFASTWrappers.writeADinputFile(ad_input_file,blade_filenames,airfoil_filenames,OLAF_filename) NumADBody = length(AD15bldNdIdxRng[:,1]) bld_len = zeros(NumADBody) - bladefileissaved = false + # bladefileissaved = false for (iADBody,filename) in enumerate(blade_filenames) strt_idx = AD15bldNdIdxRng[iADBody,1] end_idx = AD15bldNdIdxRng[iADBody,2] @@ -473,34 +507,34 @@ function setupOWENS(OWENSAero,path; ADshapeX .-= ADshapeX[1] #get it starting at zero #TODO: make robust for blades that don't start at 0 ADshapeXspl = FLOWMath.akima(LinRange(0,H,length(ADshapeX)),ADshapeX,ADshapeZ) - if iADBody<=Nbld && !bladefileissaved#Note that the blades can be curved and are assumed to be oriented vertically - bladefileissaved = true + if iADBody<=Nbld #&& !bladefileissaved#Note that the blades can be curved and are assumed to be oriented vertically + # bladefileissaved = true BlSpn0=ADshapeZ BlCrvAC0=ADshapeXspl - bladeangle = (iADBody-1)*2.0*pi/Nbld + angularOffset + bladeangle = (iADBody-1)*2.0*pi/Nbld + angularOffset #TODO: pitch offset and twist offset that isn't from the helical - BlSpn = ADshapeZ#ymesh.*sin(-bladeangle).+xmesh.*cos(-bladeangle) + BlSpn = ADshapeZ blade_twist = atan.(xmesh,ymesh).-bladeangle + #TODO: reevalueate these equations and make sure they are robust against varying designs BlCrvACinput = -ymesh.*sin(bladeangle).+xmesh.*cos(bladeangle) BlCrvACinput = BlCrvACinput .- BlCrvACinput[1] - BlCrvAC = FLOWMath.akima(LinRange(0,H,length(BlCrvACinput)),BlCrvACinput,ADshapeZ) + BlSwpAC = -FLOWMath.akima(LinRange(0,H,length(BlCrvACinput)),BlCrvACinput,ADshapeZ) BlSwpACinput = xmesh.*sin(bladeangle).+ymesh.*cos(bladeangle) BlSwpACinput = BlSwpACinput .- BlSwpACinput[1] - BlSwpAC = FLOWMath.akima(LinRange(0,H,length(BlSwpACinput)),BlSwpACinput,ADshapeZ) + BlCrvAC = FLOWMath.akima(LinRange(0,H,length(BlSwpACinput)),BlSwpACinput,ADshapeZ) - BlCrvAnginput = -blade_twist*180/pi#zeros(blade_Nnodes[iADBody]) - BlCrvAng = zeros(blade_Nnodes[iADBody])#FLOWMath.akima(LinRange(0,H,length(BlCrvAnginput)),BlCrvAnginput,ADshapeZ) + BlCrvAng = zeros(blade_Nnodes[iADBody]) BlTwistinput =(blade_twist.-blade_twist[1])*180/pi BlTwist = FLOWMath.akima(LinRange(0,H,length(BlTwistinput)),BlTwistinput,ADshapeZ) BlChord=blade_chords[iADBody] - BlAFID=collect(1:length(airfoil_filenames)) - OWENSOpenFASTWrappers.writeADbladeFile(filename;NumBlNds=blade_Nnodes[iADBody],BlSpn,BlCrvAC,BlSwpAC,BlCrvAng,BlTwist,BlChord,BlAFID) + BlAFID=collect((iADBody-1)*NumADBldNds+1:iADBody*NumADBldNds) + elseif iADBody>Nbld # while the arms/struts are assumed to be straight and are oriented by the mesh angle BlSpn=collect(LinRange(0,bld_len[iADBody],blade_Nnodes[iADBody])) BlCrvAC=zeros(blade_Nnodes[iADBody]) @@ -508,18 +542,16 @@ function setupOWENS(OWENSAero,path; BlCrvAng=zeros(blade_Nnodes[iADBody]) BlTwist=zeros(blade_Nnodes[iADBody]) BlChord=blade_chords[iADBody] - BlAFID=collect(1:length(airfoil_filenames)) - OWENSOpenFASTWrappers.writeADbladeFile(filename;NumBlNds=blade_Nnodes[iADBody],BlSpn,BlCrvAC,BlSwpAC,BlCrvAng,BlTwist,BlChord,BlAFID) - end - - + BlAFID=collect((iADBody-1)*NumADStrutNds+1:iADBody*NumADStrutNds) + end + OWENSOpenFASTWrappers.writeADbladeFile(filename;NumBlNds=blade_Nnodes[iADBody],BlSpn,BlCrvAC,BlSwpAC,BlCrvAng,BlTwist,BlChord,BlAFID) end OWENSOpenFASTWrappers.writeOLAFfile(OLAF_filename;nNWPanel=200,nFWPanels=10) OWENSOpenFASTWrappers.writeIWfile(Vinf,ifw_input_file;windINPfilename) - OWENSOpenFASTWrappers.setupTurb(adi_lib,ad_input_file,ifw_input_file,adi_rootname,[shapeX],[shapeZ],[B],[Ht],[mymesh],[myort],[AD15bldNdIdxRng],[AD15bldElIdxRng]; + OWENSOpenFASTWrappers.setupTurb(adi_lib,ad_input_file,ifw_input_file,adi_rootname,[shapeX],[shapeZ],[B],[Htwr_base],[mymesh],[myort],[AD15bldNdIdxRng],[AD15bldElIdxRng]; rho = rho, adi_dt = delta_t, adi_tmax= numTS*delta_t, @@ -531,7 +563,7 @@ function setupOWENS(OWENSAero,path; hubPos=[[0,0,0.0]], hubAngle=[[0,0,0]], nacPos=[[0,0,0]], - adi_nstrut=[2], + adi_nstrut=[Nstrutperbld], adi_debug=0, isHAWT = false # true for HAWT, false for crossflow or VAWT ) @@ -545,7 +577,7 @@ function setupOWENS(OWENSAero,path; # Calculate mass breakout of each material mass_breakout_bld = OWENS.get_material_mass(plyprops_bld,numadIn_bld) mass_breakout_blds = mass_breakout_bld.*length(mymesh.structuralNodeNumbers[:,1]) - mass_breakout_twr = OWENS.get_material_mass(plyprops_twr,numadIn_twr;int_start=0.0,int_stop=Ht) + mass_breakout_twr = OWENS.get_material_mass(plyprops_twr,numadIn_twr;int_start=0.0,int_stop=Htwr_base) if AD15On return mymesh,myel,myort,myjoint,sectionPropsArray,mass_twr, mass_bld, @@ -625,7 +657,7 @@ function setupOWENShawt(OWENSAero,path; stack_layers_scale = [1.0,1.0], chord_scale = [1.0,1.0], thickness_scale = [1.0,1.0], - Ht=2.0, + Htwr_base=2.0, ntelem = 10, #tower elements nbelem = 60, #blade elements ncelem = 10, @@ -673,7 +705,7 @@ function setupOWENShawt(OWENSAero,path; ######################################### # println("Create Mesh") if !biwing - mymesh,myort,myjoint,bladeIdx,bladeElem = create_hawt_mesh(;hub_depth=Ht, + mymesh,myort,myjoint,bladeIdx,bladeElem = create_hawt_mesh(;hub_depth=Htwr_base, tip_precone = H, #blade height R, # m bade radius AD15hubR=hubR, @@ -708,7 +740,7 @@ function setupOWENShawt(OWENSAero,path; angularOffset = -pi/2) end - nTwrElem = Int(mymesh.meshSeg[1])+2 + nTwrElem = Int(mymesh.meshSeg[1])+1 # PyPlot.figure() # PyPlot.plot(mymesh.x,mymesh.z,"b-") @@ -815,7 +847,12 @@ function setupOWENShawt(OWENSAero,path; # Get blade spanwise position bld1start = Int(mymesh.structuralNodeNumbers[1,1]) bld1end = Int(mymesh.structuralNodeNumbers[1,end]) - spanpos = [0.0;cumsum(sqrt.(diff(mymesh.x[bld1start:bld1end]).^2 .+ diff(mymesh.z[bld1start:bld1end]).^2))] + spanpos = [0.0;cumsum(sqrt.(diff(mymesh.y[bld1start:bld1end]).^2 .+ diff(mymesh.z[bld1start:bld1end]).^2))] + + #TODO: fix this, it is a hack + if biwing + spanpos = collect(LinRange(0,spanpos[end],length(spanpos)-3)) + end if length(thickness_scale)==2 yscale = collect(LinRange(thickness_scale[1],thickness_scale[2],length(numadIn_bld.span))) @@ -843,7 +880,7 @@ function setupOWENShawt(OWENSAero,path; mass_blds = collect(Iterators.flatten(fill(mass_bld, Nbld))) mass_array = [mass_twr; mass_blds] - system, assembly, sections = owens_to_gx(mymesh,myort,myjoint,sectionPropsArray,stiff_array,mass_array) + system, assembly, sections = owens_to_gx(mymesh,myort,myjoint,sectionPropsArray,stiff_array,mass_array;VTKmeshfilename="$path/vtk/HAWT_biwing") #store data in element object myel = OWENSFEA.El(sectionPropsArray,myort.Length,myort.Psi_d,myort.Theta_d,myort.Twist_d,rotationalEffects) @@ -905,7 +942,7 @@ function setupOWENShawt(OWENSAero,path; mass_breakout_bld = get_material_mass(plyprops_bld,numadIn_bld) mass_breakout_blds = mass_breakout_bld.*length(mymesh.structuralNodeNumbers[:,1]) - mass_breakout_twr = get_material_mass(plyprops_twr,numadIn_twr;int_start=0.0,int_stop=Ht) + mass_breakout_twr = get_material_mass(plyprops_twr,numadIn_twr;int_start=0.0,int_stop=Htwr_base) return mymesh,myel,myort,myjoint,sectionPropsArray,mass_twr, mass_bld, stiff_twr, stiff_bld,bld_precompinput, diff --git a/src/Unsteady_Land.jl b/src/Unsteady_Land.jl index 3742d235..32252ca2 100644 --- a/src/Unsteady_Land.jl +++ b/src/Unsteady_Land.jl @@ -324,7 +324,7 @@ function Unsteady_Land(inputs;topModel=nothing,topMesh=nothing,topEl=nothing, # genTorqueAppliedToPlatform0 = genTorqueHSS0 else if !isnothing(turbsimfile) && verbosity >=1#&& inputs.AD15On - velocity = OpenFASTWrappers.ifwcalcoutput([0.0,0.0,maximum(topMesh.z)],t[i]) + velocity = OWENSOpenFASTWrappers.ifwcalcoutput([0.0,0.0,maximum(topMesh.z)],t[i]) newVinf = velocity[1] end end diff --git a/src/meshing_utilities.jl b/src/meshing_utilities.jl index 1c90a212..40928689 100644 --- a/src/meshing_utilities.jl +++ b/src/meshing_utilities.jl @@ -267,18 +267,17 @@ function mesh_beam_centered(;L1 = 6.0, #first section of beam length end """ -return mymesh, myort, myjoint, AD15bldNdIdxRng, AD15bldElIdxRng = create_mesh_struts(;Ht = 15.0, - Hb = 147.148-15.0, #blade height +return mymesh, myort, myjoint, AD15bldNdIdxRng, AD15bldElIdxRng = create_mesh_struts(;Htwr_base = 15.0, +Htwr_blds = 147.148-15.0, + Hbld = 147.148-15.0, #blade height R = 54.014, # m bade radius AD15hubR = 2.0, nblade = 3, ntelem = 30, #tower elements nbelem = 30, #blade elements nselem = 4, - strut_twr_mountpointbot = 0.01, # This puts struts at top and bottom - strut_twr_mountpointtop = 0.99, # This puts struts at top and bottom - strut_bld_mountpointbot = 0.01, # This puts struts at top and bottom - strut_bld_mountpointtop = 0.99, # This puts struts at top and bottom + strut_twr_mountpoint = [0.01,0.5,0.9], + strut_bld_mountpoint = [0.01,0.5,0.9], bshapex = zeros(nbelem+1), #Blade shape, magnitude is irrelevant, scaled based on height and radius above bshapez = zeros(nbelem+1), bshapey = zeros(nbelem+1), # but magnitude for this is relevant @@ -290,17 +289,16 @@ return mymesh, myort, myjoint, AD15bldNdIdxRng, AD15bldElIdxRng = create_mesh_st Standard Mesh Matching 5MW, 34m configurations #Inputs -* `Ht::float`: height of tower before blades attach (m) -* `Hb::float`: blade height (m) +* `Htwr_base::float`: height of tower before blades attach (m) +* `Htwr_blds::float`: height of the tower once the blades attach (m) +* `Hbld::float`: blade height (m) * `R::float`: bade radius (m) * `nblade::int`: number of blades * `ntelem::int`: number of tower elements * `nbelem::int`: number of blade elements * `nselem::int`: number of strut elements -* `strut_twr_mountpointbot::float` = 0.01, # factor of blade height where the bottom strut attaches on the tower -* `strut_twr_mountpointtop::float` = 0.99, # factor of blade height where the top strut attaches on the tower -* `strut_bld_mountpointbot::float` = 0.01, # factor of blade height where the bottom strut attaches on the blade -* `strut_bld_mountpointtop::float` = 0.99, # factor of blade height where the top strut attaches on the blade +* `strut_twr_mountpoint::float` = [0.01,0.5,0.9], # factor of blade height where the bottom strut attaches on the tower # This puts struts at top and bottom, as a fraction of the blade position +* `strut_bld_mountpoint::float` = [0.01,0.5,0.9], # factor of blade height where the bottom strut attaches on the blade # This puts struts at bottom 0, mid 0.5, and top 1.0 as a fraction of the blade position * `bshapex::Array{<:float}`: Blade shape, magnitude is irrelevant, scaled based on height and radius above * `bshapez::Array{<:float}`: Blade shape, magnitude is irrelevant, scaled based on height and radius above * `bshapey::Array{<:float}`: Blade shape, magnitude IS relevant #TODO: resolve this @@ -317,27 +315,30 @@ Standard Mesh Matching 5MW, 34m configurations * `AD15bldNdIdxRng`: indices for start and end of all blades for AD15 (includes struts). Note that strut start nodes may be inside the strut (strut connects to tower, AD15 blade connects to hub wich is a few nodes away from tower) * `AD15bldElIdxRng`: range of elements for start and end of all AD15 blades (includes struts) """ -function create_mesh_struts(;Ht = 15.0, - Hb = 147.148-15.0, #blade height +function create_mesh_struts(;Htwr_base = 15.0, + Htwr_blds = 147.148-15.0, + Hbld = 147.148-15.0, #blade height R = 54.014, # m bade radius AD15hubR = 2.0, nblade = 3, ntelem = 30, #tower elements nbelem = 30, #blade elements nselem = 4, - strut_twr_mountpointbot = 0.01, # This puts struts at top and bottom - strut_twr_mountpointtop = 0.99, # This puts struts at top and bottom - strut_bld_mountpointbot = 0.01, # This puts struts at top and bottom - strut_bld_mountpointtop = 0.99, # This puts struts at top and bottom + strut_twr_mountpoint = [0.125,0.5,0.95], # This puts struts at top and bottom, as a fraction of the blade position + strut_bld_mountpoint = [0.25,0.5,0.75], # This puts struts at bottom 0, mid 0.5, and top 1.0 as a fraction of the blade position bshapex = zeros(nbelem+1), #Blade shape, magnitude is irrelevant, scaled based on height and radius above bshapez = zeros(nbelem+1), bshapey = zeros(nbelem+1), # but magnitude for this is relevant angularOffset = 0.0, #Blade shape, magnitude is irrelevant, scaled based on height and radius above AD15_ccw = false, - verbosity=0, # 0 nothing, 1 basic, 2 lots: amount of printed information - connectBldTips2Twr =true) + verbosity = 0, # 0 nothing, 1 basic, 2 lots: amount of printed information + connectBldTips2Twr = true) - nstrut = 2 + Nstrut = length(strut_bld_mountpoint) + + if length(strut_bld_mountpoint) != length(strut_twr_mountpoint) + error("strut_twr_mountpoint must be the same length as strut_bld_mountpoint") + end ################################## # _ @@ -347,40 +348,30 @@ function create_mesh_struts(;Ht = 15.0, #################################### ###------------Tower--------------## #################################### - mesh_z = collect(LinRange(0,Hb+Ht,ntelem+1)) + mesh_z = collect(LinRange(0,Htwr_blds+Htwr_base,ntelem+1)) # Insert mount point base - mesh_z = sort([mesh_z;Ht]) - t_botidx = findall(x->isapprox(x,Ht,atol=1e-5),mesh_z)[1]#:nblade] + mesh_z = sort([mesh_z;Htwr_base]) + t_botidx = findall(x->isapprox(x,Htwr_base,atol=1e-5),mesh_z)[1]#:nblade] - # Insert bottom strut mount point - # for ibld = 1:nblade - if maximum(Hb*strut_twr_mountpointbot+Ht .== mesh_z) # if we are at exactly an existing node, then offset our mount point + t2s_idx = zeros(Int, Nstrut) + # Insert strut mount points + for istrut = 1:Nstrut + if maximum(Hbld*strut_twr_mountpoint[istrut]+Htwr_base .== mesh_z) # if we are at exactly an existing node, then offset our mount point @warn "Mesh warning: two points are directly on top of one another, consider adjusting number of elements to space out the mesh" - strut_twr_mountpointbot += 1e-6 + strut_twr_mountpoint[istrut] += 1e-6 end - mesh_z = sort([mesh_z;Hb*strut_twr_mountpointbot+Ht]) - # end + mesh_z = sort([mesh_z;Hbld*strut_twr_mountpoint[istrut]+Htwr_base]) - # pick out the strut mounting indices - t2s_botidx = findall(x->isapprox(x,Hb*strut_twr_mountpointbot+Ht,atol=1e-5*Hb),mesh_z)[1]#:nblade] - - # Insert top strut mount point - # for ibld = 1:nblade - if maximum(Hb*(1-strut_twr_mountpointtop)+Ht .== mesh_z) # if we are at exactly an existing node, then offset our mount point - @warn "Mesh warning: two points are directly on top of one another, consider adjusting number of elements to space out the mesh" - strut_twr_mountpointtop += 1e-6 - end - mesh_z = sort([mesh_z;Hb*(1-strut_twr_mountpointtop)+Ht]) - # end + # pick out the strut mounting indices + t2s_idx[istrut] = findall(x->isapprox(x,Hbld*strut_twr_mountpoint[istrut]+Htwr_base,atol=1e-5*Hbld),mesh_z)[1] + end # Create the x and y components of same size as mesh_z now that the strut mount points are inserted mesh_x = zero(mesh_z) mesh_y = zero(mesh_z) - # pick out the strut mounting indices - t2s_topidx = findall(x->isapprox(x,Hb*(1-strut_twr_mountpointtop)+Ht,atol=1e-5*Hb),mesh_z)[1]#:nblade] - + # pick out the tower top index t_topidx = length(mesh_z) # intra-tower connectivity @@ -392,31 +383,24 @@ function create_mesh_struts(;Ht = 15.0, ###------------Blades--------------## ##################################### - #connection points on tower are simply the bottom of the tower connecting to the bottom of the blades - bld_Z = collect(LinRange(0.0,Hb,nbelem+1)) + #connection points on tower are simply the bottom of the tower offset connecting to the bottom of the blades, which is jointed if Darrieus in the joint matrix below + bld_Z = collect(LinRange(0.0,Hbld,nbelem+1)) # Insert bottom strut mount point - strut_bld_mountpointbot1 = strut_bld_mountpointbot - if maximum(Hb*strut_bld_mountpointbot .== bld_Z) # if we are at exactly an existing node, then offset our mount point - @warn "Mesh warning: two points are directly on top of one another, consider adjusting number of elements to space out the mesh" - strut_bld_mountpointbot1 -= 1e-6 - end - bld_Z = sort([bld_Z;Hb*strut_bld_mountpointbot1]) - - # Insert top strut mount point - strut_bld_mountpointtop2 = strut_bld_mountpointtop - if maximum(Hb*(1-strut_bld_mountpointtop) .== bld_Z) # if we are at exactly an existing node, then offset our mount point - @warn "Mesh warning: two points are directly on top of one another, consider adjusting number of elements to space out the mesh" - strut_bld_mountpointtop2 -= 1e-6 + for istrut = 1:Nstrut + if maximum(Hbld*strut_bld_mountpoint[istrut] .== bld_Z) # if we are at exactly an existing node, then offset our mount point + @warn "Mesh warning: two points are directly on top of one another, consider adjusting number of elements to space out the mesh" + strut_bld_mountpoint[istrut] -= 1e-6 + end + bld_Z = sort([bld_Z;Hbld*strut_bld_mountpoint[istrut]]) end - bld_Z = sort([bld_Z;Hb*(1-strut_bld_mountpointtop2)]) if bshapex == zeros(nbelem+1) - bld_Y = R.*(1.0.-4.0.*(bld_Z/Hb.-.5).^2) + bld_Y = R.*(1.0.-4.0.*(bld_Z/Hbld.-.5).^2) else # Ensure the blade shape conforms to the turbine height and radius specs bshapex = R .* bshapex./maximum(bshapex) - bshapez = Hb .* bshapez./maximum(bshapez) + bshapez = Hbld .* bshapez./maximum(bshapez) bld_Y = FLOWMath.akima(bshapez,bshapex,bld_Z) end @@ -429,7 +413,7 @@ function create_mesh_struts(;Ht = 15.0, # AeroDyn Compatability AD15bldNdIdxRng = zeros(Int64,0,2) - bld_Z .+= Ht + bld_Z .+= Htwr_base b_Z = [] b_X = [] @@ -462,9 +446,10 @@ function create_mesh_struts(;Ht = 15.0, end # pick out the strut mounting indices - b2s_botidx = findall(x->x==Hb*strut_bld_mountpointbot1+Ht,b_Z)[1:nblade] .+ length(mesh_z) - # pick out the strut mounting indices - b2s_topidx = findall(x->x==Hb*(1-strut_bld_mountpointtop2)+Ht,b_Z)[1:nblade] .+ length(mesh_z) + b2s_idx = zeros(Int,nblade,Nstrut) + for istrut = 1:Nstrut + b2s_idx[:,istrut] = findall(x->x==Hbld*strut_bld_mountpoint[istrut]+Htwr_base,b_Z)[1:nblade] .+ length(mesh_z) + end # Add to the mesh mesh_z = [mesh_z;b_Z] @@ -517,8 +502,8 @@ function create_mesh_struts(;Ht = 15.0, hubIdx += length(mesh_z) # joint connections - s2b_idx = length(mesh_z)+1 - s2t_idx = s2b_idx+length(s_z)-1 + s2b_idx_internal = length(mesh_z)+1 + s2t_idx_internal = s2b_idx_internal+length(s_z)-1 # and add to the mesh mesh_x = [mesh_x;s_x] @@ -527,30 +512,25 @@ function create_mesh_struts(;Ht = 15.0, # Intraconnectivity conn_s = zeros(nselem,2) - conn_s[:,1] = collect(s2b_idx:1:s2t_idx-1) - conn_s[:,2] = collect(s2b_idx+1:1:s2t_idx) + conn_s[:,1] = collect(s2b_idx_internal:1:s2t_idx_internal-1) + conn_s[:,2] = collect(s2b_idx_internal+1:1:s2t_idx_internal) conn = [conn;conn_s] - return s2b_idx,s2t_idx,mesh_x,mesh_y,mesh_z,conn,hubIdx + return s2b_idx_internal,s2t_idx_internal,mesh_x,mesh_y,mesh_z,conn,hubIdx end #Connect from the tower to the blades # For each blade, find the mounting location and draw a line - s2b_botidx = zeros(Int,nblade) - s2b_topidx = zeros(Int,nblade) - s2t_botidx = zeros(Int,nblade) - s2t_topidx = zeros(Int,nblade) + s2b_idx = zeros(Int,nblade,Nstrut) + s2t_idx = zeros(Int,nblade,Nstrut) # Bottom Struts - for ibld = 1:nblade - s2t_botidx[ibld],s2b_botidx[ibld],mesh_x,mesh_y,mesh_z,conn,hubIsectIdx = createstrut(t2s_botidx,b2s_botidx[ibld],mesh_x,mesh_y,mesh_z,conn,AD15hubR) - AD15bldNdIdxRng = [AD15bldNdIdxRng; hubIsectIdx s2b_botidx[ibld]] #AD15 struts always start at hub regardless of rotation, but watch out for airfoil orientation! - end - - # Top Struts - for ibld = 1:nblade - s2t_topidx[ibld],s2b_topidx[ibld],mesh_x,mesh_y,mesh_z,conn,hubIsectIdx = createstrut(t2s_topidx,b2s_topidx[ibld],mesh_x,mesh_y,mesh_z,conn,AD15hubR) - AD15bldNdIdxRng = [AD15bldNdIdxRng; hubIsectIdx s2b_topidx[ibld]] #AD15 struts always start at hub regardless of rotation, but watch out for airfoil orientation! + for istrut = 1:Nstrut + for ibld = 1:nblade + s2t_idx[ibld,istrut],s2b_idx[ibld,istrut],mesh_x,mesh_y,mesh_z,conn,hubIsectIdx = createstrut(t2s_idx[istrut],b2s_idx[ibld,istrut],mesh_x,mesh_y,mesh_z,conn,AD15hubR) + + AD15bldNdIdxRng = [AD15bldNdIdxRng; hubIsectIdx s2b_idx[ibld,istrut]] #AD15 struts always start at hub regardless of rotation, but watch out for airfoil orientation! + end end ####################################### @@ -574,15 +554,14 @@ function create_mesh_struts(;Ht = 15.0, # .bld equivalent ######################### - # For a single blade - meshSeg = zeros(Int,1+nblade+nstrut*nblade) #tower, blades, and struts + meshSeg = zeros(Int,1+nblade+Nstrut*nblade) #tower, blades, and struts if connectBldTips2Twr == false - meshSeg[1] = ntelem+nstrut+1 + meshSeg[1] = ntelem+Nstrut+1 else - meshSeg[1] = ntelem+nstrut*nblade-nblade+1 #connects at top node + meshSeg[1] = ntelem+Nstrut*nblade-nblade+1 #connects at top node end - meshSeg[2:nblade+1] .= nbelem+nstrut #+nstrut for strut mount points + meshSeg[2:nblade+1] .= nbelem+Nstrut #+Nstrut for strut mount points meshSeg[nblade+2:end] .= nselem # For each blade @@ -593,7 +572,7 @@ function create_mesh_struts(;Ht = 15.0, for iblade = 1:nblade # Normalized Span - span_len = bld_Z.-Ht#sqrt.(bld_X.^2.0.+bld_Y.^2.0.+(bld_Z.-Ht).^2.0) + span_len = bld_Z.-Htwr_base#sqrt.(bld_X.^2.0.+bld_Y.^2.0.+(bld_Z.-Htwr_base).^2.0) structuralSpanLocNorm[iblade,:] = span_len./maximum(span_len) # Node Numbers @@ -613,7 +592,7 @@ function create_mesh_struts(;Ht = 15.0, # Connect Tower Top to Blades bottom, then each cable to each blade bottom # Then each cable to each blade top, then the latter two blade tops to the first - njoint = nblade*2+nstrut*nblade*2 + njoint = nblade*2+Nstrut*nblade*2 #create the full array and then pull out zeros below if H-VAWT where the blades aren't connected to the tower. jointconn = zeros(Int,njoint,2) jointtype = zeros(njoint) for ibld = 1:nblade @@ -622,25 +601,22 @@ function create_mesh_struts(;Ht = 15.0, jointconn[ibld,:] = [t_botidx b_botidx[ibld]] end - # connect tower to strut bottom - jointconn[ibld+nblade,:] = [t2s_botidx s2t_botidx[ibld]] - - # connect tower to strut top - jointconn[ibld+nblade*2,:] = [t2s_topidx s2t_topidx[ibld]] + for istrut = 1:Nstrut + # connect tower to each strut + jointconn[ibld+nblade*istrut,:] = [t2s_idx[istrut] s2t_idx[ibld,istrut]] + end if connectBldTips2Twr # connect tower to blades tops - jointconn[ibld+nblade*3,:] = [t_topidx b_topidx[ibld]] + jointconn[ibld+nblade*(Nstrut+1),:] = [t_topidx b_topidx[ibld]] end - # connect strut to blade bottom - jointconn[ibld+nblade*4,:] = [s2b_botidx[ibld] b2s_botidx[ibld]] - - # connect strut to blade top - jointconn[ibld+nblade*5,:] = [s2b_topidx[ibld] b2s_topidx[ibld]] - + for istrut = 1:Nstrut + # connect strut to blade bottom + jointconn[ibld+nblade*(Nstrut+1+istrut),:] = [s2b_idx[ibld,istrut] b2s_idx[ibld,istrut]] + end end - + # Reduce the matrix based on if the blades got connected or not, throwing out all the zero rows bitlogic = jointconn[:,1] .!= 0.0 jointconn = jointconn[bitlogic,:] @@ -669,6 +645,7 @@ function create_mesh_struts(;Ht = 15.0, #Joint Number, Joint Connections, Joint Type, Joint Mass, Not Used, Psi_D, Theta_D myjoint = [Float64.(1:1:njoint) jointconn jointtype zeros(njoint) zeros(njoint) Psi_d_joint Theta_d_joint] + # Blade and strut starting and ending node and element numbers AD15bldElIdxRng = zeros(Int64,0,2) for i = 1:size(AD15bldNdIdxRng,1) if AD15bldNdIdxRng[i,2] > AD15bldNdIdxRng[i,1] # ascending order @@ -688,8 +665,8 @@ function create_mesh_struts(;Ht = 15.0, end """ -create_arcus_mesh(;Ht = 15.0, - Hb = 147.148-15.0, #blade height +create_arcus_mesh(;Htwr_base = 15.0, + Hbld = 147.148-15.0, #blade height R = 54.014, # m bade radius nblade = 3, ntelem = 30, #tower elements @@ -706,8 +683,8 @@ create_arcus_mesh(;Ht = 15.0, ARCUS mesh configuration: no tower between blades, no struts, but cables from top center attaching to specified blade mount point at base #Inputs -* `Ht::float`: height of tower before blades attach (m) -* `Hb::float`: blade height (m) +* `Htwr_base::float`: height of tower before blades attach (m) +* `Hbld::float`: blade height (m) * `R::float`: bade radius (m) * `nblade::int`: number of blades * `ntelem::int`: number of tower elements @@ -727,8 +704,8 @@ ARCUS mesh configuration: no tower between blades, no struts, but cables from to """ function create_arcus_mesh(; - Ht = 15.0, #tower height before blades attach - Hb = 147.148-15.0, #blade height + Htwr_base = 15.0, #tower height before blades attach + Hbld = 147.148-15.0, #blade height R = 54.014, # m bade radius nblade = 3, ntelem = 4, #tower elements @@ -751,7 +728,7 @@ function create_arcus_mesh(; #################################### ###------------Tower--------------## #################################### - mesh_z = collect(LinRange(0,Ht,ntelem+1)) + mesh_z = collect(LinRange(0,Htwr_base,ntelem+1)) # Create the x and y components mesh_x = zero(mesh_z) mesh_y = zero(mesh_z) @@ -768,25 +745,25 @@ function create_arcus_mesh(; ##################################### #connection points on tower are simply the top of the tower connecting to the bottom of the blades - bld_Z = collect(LinRange(0.0,Hb,nbelem+1)) + bld_Z = collect(LinRange(0.0,Hbld,nbelem+1)) # The cable connections must be added though - if maximum(Hb*c_mount_ratio .== bld_Z) # if we are at exactly an existing node, then offset our mount point + if maximum(Hbld*c_mount_ratio .== bld_Z) # if we are at exactly an existing node, then offset our mount point c_mount_ratio += 1e-6 end - bld_Z = sort([bld_Z;Hb*c_mount_ratio]) + bld_Z = sort([bld_Z;Hbld*c_mount_ratio]) if bshapex == zeros(nbelem+1) bshapex = R .* bshapex./maximum(bshapex) - bshapez = Hb .* bshapez./maximum(bshapez) - bld_Y = R.*(1.0.-4.0.*(bld_Z/Hb.-.5).^2) + bshapez = Hbld .* bshapez./maximum(bshapez) + bld_Y = R.*(1.0.-4.0.*(bld_Z/Hbld.-.5).^2) else # Ensure the blade shape conforms to the turbine height and radius specs bld_Y = FLOWMath.akima(bshapez,bshapex,bld_Z) end bld_X = zero(bld_Y) - bld_Z .+= Ht + bld_Z .+= Htwr_base b_Z = [] b_X = [] @@ -818,7 +795,7 @@ function create_arcus_mesh(; mesh_y = [mesh_y;b_Y] # pick out the blade to cable mounting indices - b2c_botidx = findall(x->x==Hb*c_mount_ratio+Ht,mesh_z)[1:nblade] + b2c_botidx = findall(x->x==Hbld*c_mount_ratio+Htwr_base,mesh_z)[1:nblade] ##################################### @@ -839,7 +816,7 @@ function create_arcus_mesh(; # x y z end are at the top of the tower cxend = 0.0 cyend = 0.0 - czend = Ht + Hb + czend = Htwr_base + Hbld # Now draw the lines c_x = collect(LinRange(cxstart,cxend,ncelem+1)) @@ -906,7 +883,7 @@ function create_arcus_mesh(; for iblade = 1:nblade # Normalized Span - span_len = bld_Z.-Ht#sqrt.(bld_X.^2.0.+bld_Y.^2.0.+(bld_Z.-Ht).^2.0) + span_len = bld_Z.-Htwr_base#sqrt.(bld_X.^2.0.+bld_Y.^2.0.+(bld_Z.-Htwr_base).^2.0) structuralSpanLocNorm[iblade,:] = span_len./maximum(span_len) # Node Numbers @@ -1289,8 +1266,11 @@ Takes numad formatted inputs for composite layup and material properties and run * `plyprops::plyproperties()`: see ?plyproperties for input material properties #Outputs -* `precompoutput::OWENSPreComp.Input`: see ?OWENSPreComp.Input -* `precompinput::OWENSPreComp.properties`: see ?OWENSPreComp.properties +* `precompoutput::OWENSPreComp.Output`: see ?OWENSPreComp.Input +* `precompinput::OWENSPreComp.Input`: see ?OWENSPreComp.properties +* `lam_U::Composites.Laminate`: laminate stacks used for post processing, size (n_stations, n_upper chorwise stations), upper surface, see ?Composites.Laminate +* `lam_L::Composites.Laminate`: laminate stacks used for post processing, size (n_stations, n_lower chorwise stations), lower surface, see ?Composites.Laminate +* `lam_W::Composites.Laminate`: laminate stacks used for post processing, size (n_stations, n_webs), shear webs, see ?Composites.Laminate """ function getOWENSPreCompOutput(numadIn;yscale=1.0,plyprops = plyproperties()) # Assume each station has the same number of segments and webs (some of which may be of zero width/thickness) diff --git a/src/topRunDLC.jl b/src/topRunDLC.jl index eb9a6cc1..3c2dc435 100644 --- a/src/topRunDLC.jl +++ b/src/topRunDLC.jl @@ -218,7 +218,7 @@ mass_breakout_blds,mass_breakout_twr,system,assembly,sections,AD15bldNdIdxRng, A NuMad_mat_xlscsv_file_bld,# = "$path/data/NuMAD_Materials_SNL_5MW_D_Carbon_LCDT_ThickFoils_ThinSkin.csv", NuMad_geom_xlscsv_file_strut, NuMad_mat_xlscsv_file_strut, - Ht=towerHeight, + Htwr_base=towerHeight, ntelem, nbelem, ncelem, @@ -355,464 +355,6 @@ mass_breakout_blds,mass_breakout_twr,system,assembly,sections,AD15bldNdIdxRng, A end - -function runOWENSWINDIO(WINDIO_filename,Inp,path;verbosity=2) - - windio = YAML.load_file(WINDIO_filename; dicttype=OrderedCollections.OrderedDict{Symbol,Any}) - println("Running: $(windio[:name])") - - # Assembly - # turbine_class = windio[:assembly][:turbine_class] - # turbulence_class = windio[:assembly][:turbulence_class] - # drivetrain = windio[:assembly][:drivetrain] - # rotor_orientation = windio[:assembly][:rotor_orientation] - number_of_blades = windio[:assembly][:number_of_blades] #Used - # hub_height = windio[:assembly][:hub_height] - # rotor_diameter = windio[:assembly][:rotor_diameter] - # rated_power = windio[:assembly][:rated_power] - # lifetime = windio[:assembly][:lifetime] - # marine_hydro = windio[:assembly][:marine_hydro] - - # Components - # blade_x_grid = windio[:components][:blade][:internal_structure_2d_fem][:reference_axis][:x][:grid] - blade_x = windio[:components][:blade][:internal_structure_2d_fem][:reference_axis][:x][:values] #Used - - # blade_y_grid = windio[:components][:blade][:internal_structure_2d_fem][:reference_axis][:y][:grid] - blade_y = windio[:components][:blade][:internal_structure_2d_fem][:reference_axis][:y][:values] #Used - - # blade_z_grid = windio[:components][:blade][:internal_structure_2d_fem][:reference_axis][:z][:grid] - blade_z = windio[:components][:blade][:internal_structure_2d_fem][:reference_axis][:z][:values] #Used - - # Airfoils - - # materials - - # Control - # Vin = windio[:control][:supervisory][:Vin] - # Vout = windio[:control][:supervisory][:Vout] - # maxTS = windio[:control][:supervisory][:maxTS] - - # PC_zeta = windio[:control][:pitch][:PC_zeta] - # PC_omega = windio[:control][:pitch][:PC_omega] - # ps_percent = windio[:control][:pitch][:ps_percent] - # max_pitch = windio[:control][:pitch][:max_pitch] - # max_pitch_rate = windio[:control][:pitch][:max_pitch_rate] - # min_pitch = windio[:control][:pitch][:min_pitch] - - # control_type = windio[:control][:torque][:control_type] - # tsr = windio[:control][:torque][:tsr] - # VS_zeta = windio[:control][:torque][:VS_zeta] - # VS_omega = windio[:control][:torque][:VS_omega] - # max_torque_rate = windio[:control][:torque][:max_torque_rate] - # VS_minspd = windio[:control][:torque][:VS_minspd] - # VS_maxspd = windio[:control][:torque][:VS_maxspd] - - # ss_vsgain = windio[:control][:setpoint_smooth][:ss_vsgain] - # ss_pcgain = windio[:control][:setpoint_smooth][:ss_pcgain] - - # limit_type = windio[:control][:shutdown][:limit_type] - # limit_value = windio[:control][:shutdown][:limit_value] - - # Environment - air_density = windio[:environment][:air_density] #used - air_dyn_viscosity = windio[:environment][:air_dyn_viscosity] #used - # air_speed_sound = windio[:environment][:air_speed_sound] - # shear_exp = windio[:environment][:shear_exp] - gravity = windio[:environment][:gravity] #used - # weib_shape_parameter = windio[:environment][:weib_shape_parameter] - # water_density = windio[:environment][:water_density] - # water_dyn_viscosity = windio[:environment][:water_dyn_viscosity] - # soil_shear_modulus = windio[:environment][:soil_shear_modulus] - # soil_poisson = windio[:environment][:soil_poisson] - # water_depth = windio[:environment][:water_depth] - # air_pressure = windio[:environment][:air_pressure] - # air_vapor_pressure = windio[:environment][:air_vapor_pressure] - # significant_wave_height = windio[:environment][:significant_wave_height] - # significant_wave_period = windio[:environment][:significant_wave_period] - - # BOS - # plant_turbine_spacing = windio[:bos][:plant_turbine_spacing] - # plant_row_spacing = windio[:bos][:plant_row_spacing] - # commissioning_pct = windio[:bos][:commissioning_pct] - # decommissioning_pct = windio[:bos][:decommissioning_pct] - # distance_to_substation = windio[:bos][:distance_to_substation] - # distance_to_interconnection = windio[:bos][:distance_to_interconnection] - # interconnect_voltage = windio[:bos][:interconnect_voltage] - # distance_to_site = windio[:bos][:distance_to_site] - # distance_to_landfall = windio[:bos][:distance_to_landfall] - # port_cost_per_month = windio[:bos][:port_cost_per_month] - # site_auction_price = windio[:bos][:site_auction_price] - # site_assessment_plan_cost = windio[:bos][:site_assessment_plan_cost] - # site_assessment_cost = windio[:bos][:site_assessment_cost] - # construction_operations_plan_cost = windio[:bos][:construction_operations_plan_cost] - # boem_review_cost = windio[:bos][:boem_review_cost] - # design_install_plan_cost = windio[:bos][:design_install_plan_cost] - - # Costs - # wake_loss_factor = windio[:costs][:wake_loss_factor] - # fixed_charge_rate = windio[:costs][:fixed_charge_rate] - # bos_per_kW = windio[:costs][:bos_per_kW] - # opex_per_kW = windio[:costs][:opex_per_kW] - # turbine_number = windio[:costs][:turbine_number] - # labor_rate = windio[:costs][:labor_rate] - # painting_rate = windio[:costs][:painting_rate] - # blade_mass_cost_coeff = windio[:costs][:blade_mass_cost_coeff] - # hub_mass_cost_coeff = windio[:costs][:hub_mass_cost_coeff] - # pitch_system_mass_cost_coeff = windio[:costs][:pitch_system_mass_cost_coeff] - # spinner_mass_cost_coeff = windio[:costs][:spinner_mass_cost_coeff] - # lss_mass_cost_coeff = windio[:costs][:lss_mass_cost_coeff] - # bearing_mass_cost_coeff = windio[:costs][:bearing_mass_cost_coeff] - # gearbox_mass_cost_coeff = windio[:costs][:gearbox_mass_cost_coeff] - # hss_mass_cost_coeff = windio[:costs][:hss_mass_cost_coeff] - # generator_mass_cost_coeff = windio[:costs][:generator_mass_cost_coeff] - # bedplate_mass_cost_coeff = windio[:costs][:bedplate_mass_cost_coeff] - # yaw_mass_cost_coeff = windio[:costs][:yaw_mass_cost_coeff] - # converter_mass_cost_coeff = windio[:costs][:converter_mass_cost_coeff] - # transformer_mass_cost_coeff = windio[:costs][:transformer_mass_cost_coeff] - # hvac_mass_cost_coeff = windio[:costs][:hvac_mass_cost_coeff] - # cover_mass_cost_coeff = windio[:costs][:cover_mass_cost_coeff] - # elec_connec_machine_rating_cost_coeff = windio[:costs][:elec_connec_machine_rating_cost_coeff] - # platforms_mass_cost_coeff = windio[:costs][:platforms_mass_cost_coeff] - # tower_mass_cost_coeff = windio[:costs][:tower_mass_cost_coeff] - # controls_machine_rating_cost_coeff = windio[:costs][:controls_machine_rating_cost_coeff] - # crane_cost = windio[:costs][:crane_cost] - # electricity_price = windio[:costs][:electricity_price] - # reserve_margin_price = windio[:costs][:reserve_margin_price] - # capacity_credit = windio[:costs][:capacity_credit] - # benchmark_price = windio[:costs][:benchmark_price] - - - - analysisType = Inp.analysisType - turbineType = Inp.turbineType - eta = Inp.eta - towerHeight = Inp.towerHeight - Vinf = Inp.Vinf - controlStrategy = Inp.controlStrategy - RPM = Inp.RPM - Nslices = Inp.Nslices - ntheta = Inp.ntheta - structuralModel = Inp.structuralModel - ntelem = Inp.ntelem - nbelem = Inp.nbelem - ncelem = Inp.ncelem - nselem = Inp.nselem - ifw = Inp.ifw - WindType = Inp.WindType - AModel = Inp.AModel - windINPfilename = "$(path)$(Inp.windINPfilename)" - ifw_libfile = Inp.ifw_libfile - if ifw_libfile == "nothing" - ifw_libfile = nothing - end - Blade_Height = Inp.Blade_Height # WindIO TODO: resolve DLC dependence - Blade_Radius = Inp.Blade_Radius # WindIO TODO: resolve DLC dependence - numTS = Inp.numTS - delta_t = Inp.delta_t - NuMad_geom_xlscsv_file_twr = "$(path)$(Inp.NuMad_geom_xlscsv_file_twr)" - NuMad_mat_xlscsv_file_twr = "$(path)$(Inp.NuMad_mat_xlscsv_file_twr)" - NuMad_geom_xlscsv_file_bld = "$(path)$(Inp.NuMad_geom_xlscsv_file_bld)" - NuMad_mat_xlscsv_file_bld = "$(path)$(Inp.NuMad_mat_xlscsv_file_bld)" - NuMad_geom_xlscsv_file_strut = "$(path)$(Inp.NuMad_geom_xlscsv_file_strut)" - NuMad_mat_xlscsv_file_strut = "$(path)$(Inp.NuMad_mat_xlscsv_file_strut)" - adi_lib = Inp.adi_lib - if adi_lib == "nothing" - adi_lib = nothing - end - adi_rootname = "$(path)$(Inp.adi_rootname)" - - shapeZ = blade_z#collect(LinRange(0,H,Nslices+1)) - shapeX = blade_x#R.*(1.0.-4.0.*(shapeZ/H.-.5).^2)#shapeX_spline(shapeZ) - shapeY = blade_y - - R = maximum(blade_x) #m - H = maximum(blade_z) #m - - nothing - - # Call the helper function that builds the mesh, calculates the sectional properties, - # and aligns the sectional properties to the mesh elements, - - - mymesh,myel,myort,myjoint,sectionPropsArray,mass_twr, mass_bld, - stiff_twr, stiff_bld,bld_precompinput, - bld_precompoutput,plyprops_bld,numadIn_bld,lam_U_bld,lam_L_bld, - twr_precompinput,twr_precompoutput,plyprops_twr,numadIn_twr,lam_U_twr,lam_L_twr,aeroForces,deformAero, - mass_breakout_blds,mass_breakout_twr,system,assembly,sections,AD15bldNdIdxRng, AD15bldElIdxRng = OWENS.setupOWENS(OWENSAero,path; - rho=air_density, - mu=air_dyn_viscosity, - Nslices, - ntheta, - RPM, - Vinf, - eta, - B=number_of_blades, - H, - R, - shapeZ, - shapeX, - shapeY, - ifw, - WindType, - delta_t, - numTS, - adi_lib, - adi_rootname, - windINPfilename, - ifw_libfile, - NuMad_geom_xlscsv_file_twr,# = "$path/data/NuMAD_Geom_SNL_5MW_ARCUS_Cables.csv", - NuMad_mat_xlscsv_file_twr,# = "$path/data/NuMAD_Materials_SNL_5MW_D_TaperedTower.csv", - NuMad_geom_xlscsv_file_bld,# = "$path/data/NuMAD_Geom_SNL_5MW_ARCUS.csv", - NuMad_mat_xlscsv_file_bld,# = "$path/data/NuMAD_Materials_SNL_5MW_D_Carbon_LCDT_ThickFoils_ThinSkin.csv", - NuMad_geom_xlscsv_file_strut, - NuMad_mat_xlscsv_file_strut, - Ht=towerHeight, - ntelem, - nbelem, - ncelem, - nselem, - joint_type = 0, - c_mount_ratio = 0.05, - AModel, #AD, DMS, AC - DSModel="BV", - RPI=true, - cables_connected_to_blade_base = true, - meshtype = turbineType) - - nothing - - # Optionally, we can run the finite element solver with gemetrically exact beam theory via GXBeam.jl - # this requires that the OWENS style inputs are converted to the GXBeam inputs. This interface also - # includes the ability to output VTK files, which can be viewed in paraview. We have adapted this interface - # to work with OWENS inputs as well. - - nothing - - # If the sectional properties material files includes cost information, that is combined with the density - # to estimate the overall material cost of of materials in the blades - - if verbosity>0 - - println("\nBlades' Mass Breakout") - for (i,name) in enumerate(plyprops_bld.names) - println("$name $(mass_breakout_blds[i]) kg, $(plyprops_bld.costs[i]) \$/kg: \$$(mass_breakout_blds[i]*plyprops_bld.costs[i])") - end - - println("\nTower Mass Breakout") - for (i,name) in enumerate(plyprops_twr.names) - println("$name $(mass_breakout_twr[i]) kg, $(plyprops_twr.costs[i]) \$/kg: \$$(mass_breakout_twr[i]*plyprops_twr.costs[i])") - end - - println("Total Material Cost Blades: \$$(sum(mass_breakout_blds.*plyprops_bld.costs))") - println("Total Material Cost Tower: \$$(sum(mass_breakout_twr.*plyprops_twr.costs))") - println("Total Material Cost: \$$(sum(mass_breakout_blds.*plyprops_bld.costs)+ sum(mass_breakout_twr.*plyprops_twr.costs))") - - end - - nothing - - # Here we apply the boundary conditions. For this case, with a regular cantelever tower, the tower base node which is - # 1 is constrained in all 6 degrees of freedom to have a displacement of 0. You can change this displacement to allow for things - # like pretension, and you can apply boundary conditions to any node. - - pBC = [1 1 0 - 1 2 0 - 1 3 0 - 1 4 0 - 1 5 0 - 1 6 0] - - nothing - - # There are inputs for the overall coupled simulation, please see the api reference for specifics on all the options - - if AModel=="AD" - AD15On = true - else - AD15On = false - end - - inputs = OWENS.Inputs(;analysisType = structuralModel, - tocp = [0.0,100000.1], - Omegaocp = [RPM,RPM] ./ 60, - tocp_Vinf = [0.0,100000.1], - Vinfocp = [Vinf,Vinf], - numTS, - delta_t, - AD15On, - aeroLoadsOn = 2) - - nothing - - # Then there are inputs for the finite element models, also, please see the api reference for specifics on the options (TODO: ensure that this is propogated to the docs) - - feamodel = OWENS.FEAModel(;analysisType = structuralModel, - outFilename = "none", - joint = myjoint, - platformTurbineConnectionNodeNumber = 1, - pBC, - nlOn = true, - gravityOn = [0,0,gravity], - numNodes = mymesh.numNodes, - RayleighAlpha = 0.05, - RayleighBeta = 0.05, - iterationType = "DI") - - nothing - - # Here is where we actually call the unsteady simulation and where owens pulls the aero and structural solutions together - # and propogates things in time. - - println("Running Unsteady") - t, aziHist,OmegaHist,OmegaDotHist,gbHist,gbDotHist,gbDotDotHist,FReactionHist, - FTwrBsHist,genTorque,genPower,torqueDriveShaft,uHist,uHist_prp,epsilon_x_hist,epsilon_y_hist, - epsilon_z_hist,kappa_x_hist,kappa_y_hist,kappa_z_hist = OWENS.Unsteady_Land(inputs;system,assembly, - topModel=feamodel,topMesh=mymesh,topEl=myel,aero=aeroForces,deformAero) - - nothing - - # Like described above, we can output vtk files viewable in paraview. Here it is done for each time step and shows the - # deformations. Additionaly, there is a method to input custom values and have them show up on the vtk surface mesh - # for example, strain, or reaction force, etc. This is described in more detail in the api reference for the function and: TODO - - println("Saving VTK time domain files") - OWENS.OWENSFEA_VTK("$path/vtk/SNLARCUS5MW_timedomain_TNBnltrue",t,uHist,system,assembly,sections;scaling=1,azi=aziHist) - - # println("Saving VTK time domain files") - # OWENS.OWENSFEA_VTK("$path/vtk/XFlowDeflections",t,uHist,system,assembly,sections;scaling=1,azi=aziHist) - - - # println("Saving VTK time domain files") - # userPointNames=["EA","EIyy","EIzz","e_x","e_y","e_z","k_x","k_y","k_z","Fx_Reaction","Fy_Reaction","Fz_Reaction","Mx_Reaction","My_Reaction","Mz_Reaction"]#,"Fx","Fy","Fz","Mx","My","Mz"] - # # userPointData[iname,it,ipt] = Float64 - - # # map el props to points using con - # userPointData = zeros(length(userPointNames),length(t),mymesh.numNodes) - # EA_points = zeros(mymesh.numNodes) - # EIyy_points = zeros(mymesh.numNodes) - # EIzz_points = zeros(mymesh.numNodes) - - # # Time-invariant data - # for iel = 1:length(myel.props) - # # iel = 1 - # nodes = mymesh.conn[iel,:] - # EA_points[Int.(nodes)] = myel.props[iel].EA - # EIyy_points[Int.(nodes)] = myel.props[iel].EIyy - # EIzz_points[Int.(nodes)] = myel.props[iel].EIzz - # end - - - # epsilon_x_histused = mean(epsilon_x_hist;dims=1) - # epsilon_y_histused = mean(epsilon_y_hist;dims=1) - # epsilon_z_histused = mean(epsilon_z_hist;dims=1) - # kappa_x_histused = mean(kappa_x_hist;dims=1) - # kappa_y_histused = mean(kappa_y_hist;dims=1) - # kappa_z_histused = mean(kappa_z_hist;dims=1) - - # # fill in the big matrix - # for it = 1:length(t) - - # userPointData[1,it,:] = EA_points - # userPointData[2,it,:] = EIyy_points - # userPointData[3,it,:] = EIzz_points - # for iel = 1:length(myel.props) - # nodes = mymesh.conn[iel,:] - # userPointData[4,it,Int.(nodes)] .= epsilon_x_histused[1,iel,it] - # userPointData[5,it,Int.(nodes)] .= epsilon_y_histused[1,iel,it] - # userPointData[6,it,Int.(nodes)] .= epsilon_z_histused[1,iel,it] - # userPointData[7,it,Int.(nodes)] .= kappa_x_histused[1,iel,it] - # userPointData[8,it,Int.(nodes)] .= kappa_y_histused[1,iel,it] - # userPointData[9,it,Int.(nodes)] .= kappa_z_histused[1,iel,it] - # end - # userPointData[10,it,:] .= FReactionHist[it,1:6:end] - # userPointData[11,it,:] .= FReactionHist[it,2:6:end] - # userPointData[12,it,:] .= FReactionHist[it,3:6:end] - # userPointData[13,it,:] .= FReactionHist[it,4:6:end] - # userPointData[14,it,:] .= FReactionHist[it,5:6:end] - # userPointData[15,it,:] .= FReactionHist[it,6:6:end] - - # # userPointData[4,it,:] = FReactionHist[it,1:6:end] - # # userPointData[5,it,:] = FReactionHist[it,2:6:end] - # # userPointData[6,it,:] = FReactionHist[it,3:6:end] - # # userPointData[7,it,:] = FReactionHist[it,4:6:end] - # # userPointData[8,it,:] = FReactionHist[it,5:6:end] - # # userPointData[9,it,:] = FReactionHist[it,6:6:end] - # end - - # azi=aziHist#./aziHist*1e-6 - # saveName = "$path/vtk/$(windINPfilename[1:end-4])" - # OWENS.OWENSFEA_VTK(saveName,t,uHist,system,assembly,sections;scaling=1,azi,userPointNames,userPointData) - - - nothing - - # This helper function looks through all the loads and picks out the worst case safety factor in each of the stacks of composite lamina - # it also calculates analytical simply supported buckling safety factors - - ########################################## - #### Ultimate Failure ##### - ########################################## - - massOwens,stress_U,SF_ult_U,SF_buck_U,stress_L,SF_ult_L,SF_buck_L,stress_TU,SF_ult_TU, - SF_buck_TU,stress_TL,SF_ult_TL,SF_buck_TL,topstrainout_blade_U,topstrainout_blade_L, - topstrainout_tower_U,topstrainout_tower_L,topDamage_blade_U, - topDamage_blade_L,topDamage_tower_U,topDamage_tower_L = OWENS.extractSF(bld_precompinput, - bld_precompoutput,plyprops_bld,numadIn_bld,lam_U_bld,lam_L_bld, - twr_precompinput,twr_precompoutput,plyprops_twr,numadIn_twr,lam_U_twr,lam_L_twr, - mymesh,myel,myort,number_of_blades,epsilon_x_hist,kappa_y_hist,kappa_z_hist,epsilon_z_hist, - kappa_x_hist,epsilon_y_hist;verbosity, #Verbosity 0:no printing, 1: summary, 2: summary and spanwise worst safety factor # epsilon_x_hist_1,kappa_y_hist_1,kappa_z_hist_1,epsilon_z_hist_1,kappa_x_hist_1,epsilon_y_hist_1, - LE_U_idx=1,TE_U_idx=6,SparCapU_idx=3,ForePanelU_idx=2,AftPanelU_idx=5, - LE_L_idx=1,TE_L_idx=6,SparCapL_idx=3,ForePanelL_idx=2,AftPanelL_idx=5, - Twr_LE_U_idx=1,Twr_LE_L_idx=1, - AD15bldNdIdxRng,AD15bldElIdxRng,strut_precompoutput=nothing) #TODO: add in ability to have material safety factors and load safety factors - - dataDumpFilename = "$path/InitialDataOutputs.h5" - - HDF5.h5open(dataDumpFilename, "w") do file - HDF5.write(file,"t",collect(t)) - HDF5.write(file,"aziHist",aziHist) - HDF5.write(file,"OmegaHist",OmegaHist) - HDF5.write(file,"OmegaDotHist",OmegaDotHist) - HDF5.write(file,"gbHist",gbHist) - HDF5.write(file,"gbDotHist",gbDotHist) - HDF5.write(file,"gbDotDotHist",gbDotDotHist) - HDF5.write(file,"FReactionHist",FReactionHist) - HDF5.write(file,"FTwrBsHist",FTwrBsHist) - HDF5.write(file,"genTorque",genTorque) - HDF5.write(file,"genPower",genPower) - HDF5.write(file,"torqueDriveShaft",torqueDriveShaft) - HDF5.write(file,"uHist",uHist) - HDF5.write(file,"uHist_prp",uHist_prp) - HDF5.write(file,"epsilon_x_hist",epsilon_x_hist) - HDF5.write(file,"epsilon_y_hist",epsilon_y_hist) - HDF5.write(file,"epsilon_z_hist",epsilon_z_hist) - HDF5.write(file,"kappa_x_hist",kappa_x_hist) - HDF5.write(file,"kappa_y_hist",kappa_y_hist) - HDF5.write(file,"kappa_z_hist",kappa_z_hist) - HDF5.write(file,"massOwens",massOwens) - HDF5.write(file,"stress_U",stress_U) - HDF5.write(file,"SF_ult_U",SF_ult_U) - HDF5.write(file,"SF_buck_U",SF_buck_U) - HDF5.write(file,"stress_L",stress_L) - HDF5.write(file,"SF_ult_L",SF_ult_L) - HDF5.write(file,"SF_buck_L",SF_buck_L) - HDF5.write(file,"stress_TU",stress_TU) - HDF5.write(file,"SF_ult_TU",SF_ult_TU) - HDF5.write(file,"SF_buck_TU",SF_buck_TU) - HDF5.write(file,"stress_TL",stress_TL) - HDF5.write(file,"SF_ult_TL",SF_ult_TL) - HDF5.write(file,"SF_buck_TL",SF_buck_TL) - HDF5.write(file,"topstrainout_blade_U",topstrainout_blade_U) - HDF5.write(file,"topstrainout_blade_L",topstrainout_blade_L) - HDF5.write(file,"topstrainout_tower_U",topstrainout_tower_U) - HDF5.write(file,"topstrainout_tower_L",topstrainout_tower_L) - HDF5.write(file,"topDamage_blade_U",topDamage_blade_U) - HDF5.write(file,"topDamage_blade_L",topDamage_blade_L) - HDF5.write(file,"topDamage_tower_U",topDamage_tower_U) - HDF5.write(file,"topDamage_tower_L",topDamage_tower_L) - end -end - # # Test # Inp = OWENS.MasterInput(;numTS=3,ifw_libfile="$localpath/../../openfastandy/build/modules/inflowwind/libifw_c_binding") # OWENS.runDLC(["1_1","1_2"],Inp,localpath;Vinf_range=LinRange(5,20,2),regenWindFiles=true,pathtoturbsim="$localpath/../../openfastandy/build/modules/turbsim/turbsim") diff --git a/src/windio.jl b/src/windio.jl new file mode 100644 index 00000000..f10035be --- /dev/null +++ b/src/windio.jl @@ -0,0 +1,460 @@ + +function runOWENSWINDIO(windio,Inp,path;verbosity=2) + if typeof(windio) == String + windio = YAML.load_file(windio; dicttype=OrderedCollections.OrderedDict{Symbol,Any}) + println("Running: $(windio[:name])") + end + + # Assembly + # turbine_class = windio[:assembly][:turbine_class] + # turbulence_class = windio[:assembly][:turbulence_class] + # drivetrain = windio[:assembly][:drivetrain] + # rotor_orientation = windio[:assembly][:rotor_orientation] + number_of_blades = windio[:assembly][:number_of_blades] #Used + # hub_height = windio[:assembly][:hub_height] + # rotor_diameter = windio[:assembly][:rotor_diameter] + # rated_power = windio[:assembly][:rated_power] + # lifetime = windio[:assembly][:lifetime] + # marine_hydro = windio[:assembly][:marine_hydro] + + # Components + # blade_x_grid = windio[:components][:blade][:internal_structure_2d_fem][:reference_axis][:x][:grid] + blade_x = windio[:components][:blade][:internal_structure_2d_fem][:reference_axis][:x][:values] #Used + + # blade_y_grid = windio[:components][:blade][:internal_structure_2d_fem][:reference_axis][:y][:grid] + blade_y = windio[:components][:blade][:internal_structure_2d_fem][:reference_axis][:y][:values] #Used + + # blade_z_grid = windio[:components][:blade][:internal_structure_2d_fem][:reference_axis][:z][:grid] + blade_z = windio[:components][:blade][:internal_structure_2d_fem][:reference_axis][:z][:values] #Used + + # Airfoils + + # materials + + # Control + # Vin = windio[:control][:supervisory][:Vin] + # Vout = windio[:control][:supervisory][:Vout] + # maxTS = windio[:control][:supervisory][:maxTS] + + # PC_zeta = windio[:control][:pitch][:PC_zeta] + # PC_omega = windio[:control][:pitch][:PC_omega] + # ps_percent = windio[:control][:pitch][:ps_percent] + # max_pitch = windio[:control][:pitch][:max_pitch] + # max_pitch_rate = windio[:control][:pitch][:max_pitch_rate] + # min_pitch = windio[:control][:pitch][:min_pitch] + + # control_type = windio[:control][:torque][:control_type] + # tsr = windio[:control][:torque][:tsr] + # VS_zeta = windio[:control][:torque][:VS_zeta] + # VS_omega = windio[:control][:torque][:VS_omega] + # max_torque_rate = windio[:control][:torque][:max_torque_rate] + # VS_minspd = windio[:control][:torque][:VS_minspd] + # VS_maxspd = windio[:control][:torque][:VS_maxspd] + + # ss_vsgain = windio[:control][:setpoint_smooth][:ss_vsgain] + # ss_pcgain = windio[:control][:setpoint_smooth][:ss_pcgain] + + # limit_type = windio[:control][:shutdown][:limit_type] + # limit_value = windio[:control][:shutdown][:limit_value] + + # Environment + air_density = windio[:environment][:air_density] #used + air_dyn_viscosity = windio[:environment][:air_dyn_viscosity] #used + # air_speed_sound = windio[:environment][:air_speed_sound] + # shear_exp = windio[:environment][:shear_exp] + gravity = windio[:environment][:gravity] #used + # weib_shape_parameter = windio[:environment][:weib_shape_parameter] + # water_density = windio[:environment][:water_density] + # water_dyn_viscosity = windio[:environment][:water_dyn_viscosity] + # soil_shear_modulus = windio[:environment][:soil_shear_modulus] + # soil_poisson = windio[:environment][:soil_poisson] + # water_depth = windio[:environment][:water_depth] + # air_pressure = windio[:environment][:air_pressure] + # air_vapor_pressure = windio[:environment][:air_vapor_pressure] + # significant_wave_height = windio[:environment][:significant_wave_height] + # significant_wave_period = windio[:environment][:significant_wave_period] + + # BOS + # plant_turbine_spacing = windio[:bos][:plant_turbine_spacing] + # plant_row_spacing = windio[:bos][:plant_row_spacing] + # commissioning_pct = windio[:bos][:commissioning_pct] + # decommissioning_pct = windio[:bos][:decommissioning_pct] + # distance_to_substation = windio[:bos][:distance_to_substation] + # distance_to_interconnection = windio[:bos][:distance_to_interconnection] + # interconnect_voltage = windio[:bos][:interconnect_voltage] + # distance_to_site = windio[:bos][:distance_to_site] + # distance_to_landfall = windio[:bos][:distance_to_landfall] + # port_cost_per_month = windio[:bos][:port_cost_per_month] + # site_auction_price = windio[:bos][:site_auction_price] + # site_assessment_plan_cost = windio[:bos][:site_assessment_plan_cost] + # site_assessment_cost = windio[:bos][:site_assessment_cost] + # construction_operations_plan_cost = windio[:bos][:construction_operations_plan_cost] + # boem_review_cost = windio[:bos][:boem_review_cost] + # design_install_plan_cost = windio[:bos][:design_install_plan_cost] + + # Costs + # wake_loss_factor = windio[:costs][:wake_loss_factor] + # fixed_charge_rate = windio[:costs][:fixed_charge_rate] + # bos_per_kW = windio[:costs][:bos_per_kW] + # opex_per_kW = windio[:costs][:opex_per_kW] + # turbine_number = windio[:costs][:turbine_number] + # labor_rate = windio[:costs][:labor_rate] + # painting_rate = windio[:costs][:painting_rate] + # blade_mass_cost_coeff = windio[:costs][:blade_mass_cost_coeff] + # hub_mass_cost_coeff = windio[:costs][:hub_mass_cost_coeff] + # pitch_system_mass_cost_coeff = windio[:costs][:pitch_system_mass_cost_coeff] + # spinner_mass_cost_coeff = windio[:costs][:spinner_mass_cost_coeff] + # lss_mass_cost_coeff = windio[:costs][:lss_mass_cost_coeff] + # bearing_mass_cost_coeff = windio[:costs][:bearing_mass_cost_coeff] + # gearbox_mass_cost_coeff = windio[:costs][:gearbox_mass_cost_coeff] + # hss_mass_cost_coeff = windio[:costs][:hss_mass_cost_coeff] + # generator_mass_cost_coeff = windio[:costs][:generator_mass_cost_coeff] + # bedplate_mass_cost_coeff = windio[:costs][:bedplate_mass_cost_coeff] + # yaw_mass_cost_coeff = windio[:costs][:yaw_mass_cost_coeff] + # converter_mass_cost_coeff = windio[:costs][:converter_mass_cost_coeff] + # transformer_mass_cost_coeff = windio[:costs][:transformer_mass_cost_coeff] + # hvac_mass_cost_coeff = windio[:costs][:hvac_mass_cost_coeff] + # cover_mass_cost_coeff = windio[:costs][:cover_mass_cost_coeff] + # elec_connec_machine_rating_cost_coeff = windio[:costs][:elec_connec_machine_rating_cost_coeff] + # platforms_mass_cost_coeff = windio[:costs][:platforms_mass_cost_coeff] + # tower_mass_cost_coeff = windio[:costs][:tower_mass_cost_coeff] + # controls_machine_rating_cost_coeff = windio[:costs][:controls_machine_rating_cost_coeff] + # crane_cost = windio[:costs][:crane_cost] + # electricity_price = windio[:costs][:electricity_price] + # reserve_margin_price = windio[:costs][:reserve_margin_price] + # capacity_credit = windio[:costs][:capacity_credit] + # benchmark_price = windio[:costs][:benchmark_price] + + + + analysisType = Inp.analysisType + turbineType = Inp.turbineType + eta = Inp.eta + towerHeight = Inp.towerHeight + Vinf = Inp.Vinf + controlStrategy = Inp.controlStrategy + RPM = Inp.RPM + Nslices = Inp.Nslices + ntheta = Inp.ntheta + structuralModel = Inp.structuralModel + ntelem = Inp.ntelem + nbelem = Inp.nbelem + ncelem = Inp.ncelem + nselem = Inp.nselem + ifw = Inp.ifw + WindType = Inp.WindType + AModel = Inp.AModel + windINPfilename = "$(path)$(Inp.windINPfilename)" + ifw_libfile = Inp.ifw_libfile + if ifw_libfile == "nothing" + ifw_libfile = nothing + end + Blade_Height = Inp.Blade_Height # WindIO TODO: resolve DLC dependence + Blade_Radius = Inp.Blade_Radius # WindIO TODO: resolve DLC dependence + numTS = Inp.numTS + delta_t = Inp.delta_t + NuMad_geom_xlscsv_file_twr = "$(path)$(Inp.NuMad_geom_xlscsv_file_twr)" + NuMad_mat_xlscsv_file_twr = "$(path)$(Inp.NuMad_mat_xlscsv_file_twr)" + NuMad_geom_xlscsv_file_bld = "$(path)$(Inp.NuMad_geom_xlscsv_file_bld)" + NuMad_mat_xlscsv_file_bld = "$(path)$(Inp.NuMad_mat_xlscsv_file_bld)" + NuMad_geom_xlscsv_file_strut = "$(path)$(Inp.NuMad_geom_xlscsv_file_strut)" + NuMad_mat_xlscsv_file_strut = "$(path)$(Inp.NuMad_mat_xlscsv_file_strut)" + adi_lib = Inp.adi_lib + if adi_lib == "nothing" + adi_lib = nothing + end + adi_rootname = "$(path)$(Inp.adi_rootname)" + + shapeZ = blade_z#collect(LinRange(0,H,Nslices+1)) + shapeX = blade_x#R.*(1.0.-4.0.*(shapeZ/H.-.5).^2)#shapeX_spline(shapeZ) + shapeY = blade_y + + R = maximum(blade_x) #m + H = maximum(blade_z) #m + + nothing + + # Call the helper function that builds the mesh, calculates the sectional properties, + # and aligns the sectional properties to the mesh elements, + + + mymesh,myel,myort,myjoint,sectionPropsArray,mass_twr, mass_bld, + stiff_twr, stiff_bld,bld_precompinput, + bld_precompoutput,plyprops_bld,numadIn_bld,lam_U_bld,lam_L_bld, + twr_precompinput,twr_precompoutput,plyprops_twr,numadIn_twr,lam_U_twr,lam_L_twr,aeroForces,deformAero, + mass_breakout_blds,mass_breakout_twr,system,assembly,sections,AD15bldNdIdxRng, AD15bldElIdxRng = OWENS.setupOWENS(OWENSAero,path; + rho=air_density, + mu=air_dyn_viscosity, + Nslices, + ntheta, + RPM, + Vinf, + eta, + B=number_of_blades, + H, + R, + shapeZ, + shapeX, + shapeY, + ifw, + WindType, + delta_t, + numTS, + adi_lib, + adi_rootname, + windINPfilename, + ifw_libfile, + NuMad_geom_xlscsv_file_twr,# = "$path/data/NuMAD_Geom_SNL_5MW_ARCUS_Cables.csv", + NuMad_mat_xlscsv_file_twr,# = "$path/data/NuMAD_Materials_SNL_5MW_D_TaperedTower.csv", + NuMad_geom_xlscsv_file_bld,# = "$path/data/NuMAD_Geom_SNL_5MW_ARCUS.csv", + NuMad_mat_xlscsv_file_bld,# = "$path/data/NuMAD_Materials_SNL_5MW_D_Carbon_LCDT_ThickFoils_ThinSkin.csv", + NuMad_geom_xlscsv_file_strut, + NuMad_mat_xlscsv_file_strut, + Htwr_base=towerHeight, + ntelem, + nbelem, + ncelem, + nselem, + joint_type = 0, + c_mount_ratio = 0.05, + strut_twr_mountpoint = [0.03,0.97], + strut_bld_mountpoint = [0.03,0.97], + AModel, #AD, DMS, AC + DSModel="BV", + RPI=true, + cables_connected_to_blade_base = true, + meshtype = turbineType) + + nothing + + # Optionally, we can run the finite element solver with gemetrically exact beam theory via GXBeam.jl + # this requires that the OWENS style inputs are converted to the GXBeam inputs. This interface also + # includes the ability to output VTK files, which can be viewed in paraview. We have adapted this interface + # to work with OWENS inputs as well. + + nothing + + # If the sectional properties material files includes cost information, that is combined with the density + # to estimate the overall material cost of of materials in the blades + + if verbosity>0 + + println("\nBlades' Mass Breakout") + for (i,name) in enumerate(plyprops_bld.names) + println("$name $(mass_breakout_blds[i]) kg, $(plyprops_bld.costs[i]) \$/kg: \$$(mass_breakout_blds[i]*plyprops_bld.costs[i])") + end + + println("\nTower Mass Breakout") + for (i,name) in enumerate(plyprops_twr.names) + println("$name $(mass_breakout_twr[i]) kg, $(plyprops_twr.costs[i]) \$/kg: \$$(mass_breakout_twr[i]*plyprops_twr.costs[i])") + end + + println("Total Material Cost Blades: \$$(sum(mass_breakout_blds.*plyprops_bld.costs))") + println("Total Material Cost Tower: \$$(sum(mass_breakout_twr.*plyprops_twr.costs))") + println("Total Material Cost: \$$(sum(mass_breakout_blds.*plyprops_bld.costs)+ sum(mass_breakout_twr.*plyprops_twr.costs))") + + end + + nothing + + # Here we apply the boundary conditions. For this case, with a regular cantelever tower, the tower base node which is + # 1 is constrained in all 6 degrees of freedom to have a displacement of 0. You can change this displacement to allow for things + # like pretension, and you can apply boundary conditions to any node. + + pBC = [1 1 0 + 1 2 0 + 1 3 0 + 1 4 0 + 1 5 0 + 1 6 0] + + nothing + + # There are inputs for the overall coupled simulation, please see the api reference for specifics on all the options + + if AModel=="AD" + AD15On = true + else + AD15On = false + end + + inputs = OWENS.Inputs(;analysisType = structuralModel, + tocp = [0.0,100000.1], + Omegaocp = [RPM,RPM] ./ 60, + tocp_Vinf = [0.0,100000.1], + Vinfocp = [Vinf,Vinf], + numTS, + delta_t, + AD15On, + aeroLoadsOn = 2) + + nothing + + # Then there are inputs for the finite element models, also, please see the api reference for specifics on the options (TODO: ensure that this is propogated to the docs) + + feamodel = OWENS.FEAModel(;analysisType = structuralModel, + outFilename = "none", + joint = myjoint, + platformTurbineConnectionNodeNumber = 1, + pBC, + nlOn = true, + # gravityOn = [0,0,gravity], + numNodes = mymesh.numNodes, + RayleighAlpha = 0.05, + RayleighBeta = 0.05, + iterationType = "DI") + + nothing + + # Here is where we actually call the unsteady simulation and where owens pulls the aero and structural solutions together + # and propogates things in time. + + println("Running Unsteady") + t, aziHist,OmegaHist,OmegaDotHist,gbHist,gbDotHist,gbDotDotHist,FReactionHist, + FTwrBsHist,genTorque,genPower,torqueDriveShaft,uHist,uHist_prp,epsilon_x_hist,epsilon_y_hist, + epsilon_z_hist,kappa_x_hist,kappa_y_hist,kappa_z_hist = OWENS.Unsteady_Land(inputs;system,assembly, + topModel=feamodel,topMesh=mymesh,topEl=myel,aero=aeroForces,deformAero) + + nothing + + # Like described above, we can output vtk files viewable in paraview. Here it is done for each time step and shows the + # deformations. Additionaly, there is a method to input custom values and have them show up on the vtk surface mesh + # for example, strain, or reaction force, etc. This is described in more detail in the api reference for the function and: TODO + + println("Saving VTK time domain files") + # OWENS.OWENSFEA_VTK("$path/vtk/Initial_timedomain",t,uHist,system,assembly,sections;scaling=1,azi=aziHist) + + # println("Saving VTK time domain files") + # OWENS.OWENSFEA_VTK("$path/vtk/XFlowDeflections",t,uHist,system,assembly,sections;scaling=1,azi=aziHist) + + + # println("Saving VTK time domain files") + # userPointNames=["EA","EIyy","EIzz","e_x","e_y","e_z","k_x","k_y","k_z","Fx_Reaction","Fy_Reaction","Fz_Reaction","Mx_Reaction","My_Reaction","Mz_Reaction"]#,"Fx","Fy","Fz","Mx","My","Mz"] + # # userPointData[iname,it,ipt] = Float64 + + # # map el props to points using con + # userPointData = zeros(length(userPointNames),length(t),mymesh.numNodes) + # EA_points = zeros(mymesh.numNodes) + # EIyy_points = zeros(mymesh.numNodes) + # EIzz_points = zeros(mymesh.numNodes) + + # # Time-invariant data + # for iel = 1:length(myel.props) + # # iel = 1 + # nodes = mymesh.conn[iel,:] + # EA_points[Int.(nodes)] = myel.props[iel].EA + # EIyy_points[Int.(nodes)] = myel.props[iel].EIyy + # EIzz_points[Int.(nodes)] = myel.props[iel].EIzz + # end + + + # epsilon_x_histused = mean(epsilon_x_hist;dims=1) + # epsilon_y_histused = mean(epsilon_y_hist;dims=1) + # epsilon_z_histused = mean(epsilon_z_hist;dims=1) + # kappa_x_histused = mean(kappa_x_hist;dims=1) + # kappa_y_histused = mean(kappa_y_hist;dims=1) + # kappa_z_histused = mean(kappa_z_hist;dims=1) + + # # fill in the big matrix + # for it = 1:length(t) + + # userPointData[1,it,:] = EA_points + # userPointData[2,it,:] = EIyy_points + # userPointData[3,it,:] = EIzz_points + # for iel = 1:length(myel.props) + # nodes = mymesh.conn[iel,:] + # userPointData[4,it,Int.(nodes)] .= epsilon_x_histused[1,iel,it] + # userPointData[5,it,Int.(nodes)] .= epsilon_y_histused[1,iel,it] + # userPointData[6,it,Int.(nodes)] .= epsilon_z_histused[1,iel,it] + # userPointData[7,it,Int.(nodes)] .= kappa_x_histused[1,iel,it] + # userPointData[8,it,Int.(nodes)] .= kappa_y_histused[1,iel,it] + # userPointData[9,it,Int.(nodes)] .= kappa_z_histused[1,iel,it] + # end + # userPointData[10,it,:] .= FReactionHist[it,1:6:end] + # userPointData[11,it,:] .= FReactionHist[it,2:6:end] + # userPointData[12,it,:] .= FReactionHist[it,3:6:end] + # userPointData[13,it,:] .= FReactionHist[it,4:6:end] + # userPointData[14,it,:] .= FReactionHist[it,5:6:end] + # userPointData[15,it,:] .= FReactionHist[it,6:6:end] + + # # userPointData[4,it,:] = FReactionHist[it,1:6:end] + # # userPointData[5,it,:] = FReactionHist[it,2:6:end] + # # userPointData[6,it,:] = FReactionHist[it,3:6:end] + # # userPointData[7,it,:] = FReactionHist[it,4:6:end] + # # userPointData[8,it,:] = FReactionHist[it,5:6:end] + # # userPointData[9,it,:] = FReactionHist[it,6:6:end] + # end + + # azi=aziHist#./aziHist*1e-6 + # saveName = "$path/vtk/$(windINPfilename[1:end-4])" + # OWENS.OWENSFEA_VTK(saveName,t,uHist,system,assembly,sections;scaling=1,azi,userPointNames,userPointData) + + + nothing + + # This helper function looks through all the loads and picks out the worst case safety factor in each of the stacks of composite lamina + # it also calculates analytical simply supported buckling safety factors + + ########################################## + #### Ultimate Failure ##### + ########################################## + + massOwens,stress_U,SF_ult_U,SF_buck_U,stress_L,SF_ult_L,SF_buck_L,stress_TU,SF_ult_TU, + SF_buck_TU,stress_TL,SF_ult_TL,SF_buck_TL,topstrainout_blade_U,topstrainout_blade_L, + topstrainout_tower_U,topstrainout_tower_L,topDamage_blade_U, + topDamage_blade_L,topDamage_tower_U,topDamage_tower_L = OWENS.extractSF(bld_precompinput, + bld_precompoutput,plyprops_bld,numadIn_bld,lam_U_bld,lam_L_bld, + twr_precompinput,twr_precompoutput,plyprops_twr,numadIn_twr,lam_U_twr,lam_L_twr, + mymesh,myel,myort,number_of_blades,epsilon_x_hist,kappa_y_hist,kappa_z_hist,epsilon_z_hist, + kappa_x_hist,epsilon_y_hist;verbosity, #Verbosity 0:no printing, 1: summary, 2: summary and spanwise worst safety factor # epsilon_x_hist_1,kappa_y_hist_1,kappa_z_hist_1,epsilon_z_hist_1,kappa_x_hist_1,epsilon_y_hist_1, + LE_U_idx=1,TE_U_idx=6,SparCapU_idx=3,ForePanelU_idx=2,AftPanelU_idx=5, + LE_L_idx=1,TE_L_idx=6,SparCapL_idx=3,ForePanelL_idx=2,AftPanelL_idx=5, + Twr_LE_U_idx=1,Twr_LE_L_idx=1, + AD15bldNdIdxRng,AD15bldElIdxRng,strut_precompoutput=nothing) #TODO: add in ability to have material safety factors and load safety factors + + dataDumpFilename = "$path/InitialDataOutputs.h5" + + HDF5.h5open(dataDumpFilename, "w") do file + HDF5.write(file,"t",collect(t)) + HDF5.write(file,"aziHist",aziHist) + HDF5.write(file,"OmegaHist",OmegaHist) + HDF5.write(file,"OmegaDotHist",OmegaDotHist) + HDF5.write(file,"gbHist",gbHist) + HDF5.write(file,"gbDotHist",gbDotHist) + HDF5.write(file,"gbDotDotHist",gbDotDotHist) + HDF5.write(file,"FReactionHist",FReactionHist) + HDF5.write(file,"FTwrBsHist",FTwrBsHist) + HDF5.write(file,"genTorque",genTorque) + HDF5.write(file,"genPower",genPower) + HDF5.write(file,"torqueDriveShaft",torqueDriveShaft) + HDF5.write(file,"uHist",uHist) + HDF5.write(file,"uHist_prp",uHist_prp) + HDF5.write(file,"epsilon_x_hist",epsilon_x_hist) + HDF5.write(file,"epsilon_y_hist",epsilon_y_hist) + HDF5.write(file,"epsilon_z_hist",epsilon_z_hist) + HDF5.write(file,"kappa_x_hist",kappa_x_hist) + HDF5.write(file,"kappa_y_hist",kappa_y_hist) + HDF5.write(file,"kappa_z_hist",kappa_z_hist) + HDF5.write(file,"massOwens",massOwens) + HDF5.write(file,"stress_U",stress_U) + HDF5.write(file,"SF_ult_U",SF_ult_U) + HDF5.write(file,"SF_buck_U",SF_buck_U) + HDF5.write(file,"stress_L",stress_L) + HDF5.write(file,"SF_ult_L",SF_ult_L) + HDF5.write(file,"SF_buck_L",SF_buck_L) + HDF5.write(file,"stress_TU",stress_TU) + HDF5.write(file,"SF_ult_TU",SF_ult_TU) + HDF5.write(file,"SF_buck_TU",SF_buck_TU) + HDF5.write(file,"stress_TL",stress_TL) + HDF5.write(file,"SF_ult_TL",SF_ult_TL) + HDF5.write(file,"SF_buck_TL",SF_buck_TL) + HDF5.write(file,"topstrainout_blade_U",topstrainout_blade_U) + HDF5.write(file,"topstrainout_blade_L",topstrainout_blade_L) + HDF5.write(file,"topstrainout_tower_U",topstrainout_tower_U) + HDF5.write(file,"topstrainout_tower_L",topstrainout_tower_L) + HDF5.write(file,"topDamage_blade_U",topDamage_blade_U) + HDF5.write(file,"topDamage_blade_L",topDamage_blade_L) + HDF5.write(file,"topDamage_tower_U",topDamage_tower_U) + HDF5.write(file,"topDamage_tower_L",topDamage_tower_L) + end +end \ No newline at end of file diff --git a/test/Fig4_5_campbell2.jl b/test/Fig4_5_campbell2.jl index 08280425..f569cba0 100644 --- a/test/Fig4_5_campbell2.jl +++ b/test/Fig4_5_campbell2.jl @@ -125,14 +125,14 @@ mass_breakout_blds,mass_breakout_twr,system, assembly, sections = OWENS.setupOWE NuMad_mat_xlscsv_file_bld,# = "$path/data/NuMAD_Materials_SNL_5MW_D_Carbon_LCDT_ThickFoils_ThinSkin.csv", NuMad_geom_xlscsv_file_strut, NuMad_mat_xlscsv_file_strut, - Ht=towerHeight, + Htwr_base=towerHeight, ntelem, nbelem, ncelem, nselem, joint_type = 0, - strut_mountpointbot = 0.03, - strut_mountpointtop = 0.03, + strut_twr_mountpoint = [0.03,0.97], + strut_bld_mountpoint = [0.03,0.97], AModel, #AD, DMS, AC DSModel="BV", RPI=true, diff --git a/test/check_mesh.jl b/test/check_mesh.jl index 7d2dbd9f..cf05081d 100644 --- a/test/check_mesh.jl +++ b/test/check_mesh.jl @@ -14,18 +14,16 @@ joint = DelimitedFiles.readdlm("$(path)/data/unit_test_5MW.jnt",'\t',skipstart = SNL5MW_bld_z = [15.0, 21.61004296, 28.20951408, 28.2148, 34.81955704, 41.4296, 48.03964296, 54.63911408, 61.24915704, 67.8592, 74.46924296, 81.06871408, 87.67875704, 94.2888, 100.89884296, 107.49831408, 114.10835704, 120.7184, 127.32844296, 133.92791408, 133.9332, 140.53795704, 147.148].-15.0 SNL5MW_bld_x = -[0.0, -10.201, -20.361, -20.368290684, -29.478, -36.575, -42.579, -47.177, -50.555, -52.809, -53.953, -54.014, -53.031, -51.024, -47.979, -43.942, -38.768, -32.91, -25.587, -17.587, -17.580079568, -8.933, 8.0917312607e-15] -mymesh,myort,myjoint = OWENS.create_mesh_struts(;Ht=15.0, -Hb = 147.148-15.0, #blade height +mymesh,myort,myjoint = OWENS.create_mesh_struts(;Htwr_base=15.0, +Hbld = 147.148-15.0, #blade height R = 54.014, # m bade radius nblade = 2, AD15hubR=0.0, ntelem = 20, #tower elements nbelem = 20, #blade elements nselem = 2, -strut_twr_mountpointbot = 0.1, -strut_twr_mountpointtop = 0.1, -strut_bld_mountpointbot = 0.1, -strut_bld_mountpointtop = 0.1, +strut_twr_mountpoint = [0.1,0.9], +strut_bld_mountpoint = [0.1,0.9], bshapex = SNL5MW_bld_x, #Blade shape, magnitude is irrelevant, scaled based on height and radius above bshapez = SNL5MW_bld_z, angularOffset = -pi/2) #Blade shape, magnitude is irrelevant, scaled based on height and radius above @@ -78,6 +76,9 @@ end # sleep(0.2) # end +# PyPlot.scatter3D(mymesh.x,mymesh.y,mymesh.z) +# PyPlot.scatter3D(mesh.x,mesh.y,mesh.z) + # PyPlot.figure() # PyPlot.plot(mymesh.y,mymesh.z,"k.-",markersize=10.0) # PyPlot.plot(mesh.y,mesh.z,"b.")