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driver.py
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import sys
sys.path.append("./aerodynamic")
from getLoad import getLoad
import numpy as np
# ================================
# Preprocessing
# ================================
# --------------------------------
# Compute geometry and CL_factor
# --------------------------------
raw_data = np.array(
[[22.98279158699809, 0.0],
[36.59655831739962, 0.0],
[25.08728179551122, 2.8336658354114803],
[36.957605985037404, 2.8336658354114803],
[31.07231920199501, 10.866832917705743],
[38.35411471321696, 10.866832917705743],
[45.137157107231914, 29.390523690773072],
[47.83042394014963, 29.390523690773072]])
raw_data = raw_data - raw_data[0, :]
# chord
chord0 = raw_data[1, 0] - raw_data[0, 0]
chord1 = raw_data[3, 0] - raw_data[2, 0]
chord2 = raw_data[5, 0] - raw_data[4, 0]
chord3 = raw_data[7, 0] - raw_data[6, 0]
dh_01 = raw_data[2, 1] - raw_data[0, 1]
dh_12 = raw_data[4, 1] - raw_data[2, 1]
dh_23 = raw_data[6, 1] - raw_data[4, 1]
print("raw_data", raw_data)
print("chord0", chord0)
print("chord1", chord1)
print("chord2", chord2)
print("chord3", chord3)
print("dh_01", dh_01)
print("dh_12", dh_12)
print("dh_23", dh_23)
# area
area0 = (chord0 + chord1)/2 * dh_01
area1 = (chord1 + chord2)/2 * dh_12
area2 = (chord2 + chord3)/2 * dh_23
print("area0", area0)
print("area1", area1)
print("area2", area2)
area_aero = (area1 + area2) * 2
area_ref = (area0 + area1 + area2) * 2
CL_factor = area_ref / area_aero
print("area_aero", area_aero)
print("area_ref", area_ref)
print("CL_factor", CL_factor)
# span
span = raw_data[-1, 1]*2
print("span", span)
# --------------------------------
# Compute 2.5 g CL
# --------------------------------
# parameters
MTOW = 297500 # kg
Area = 410.8 # m^2 reference area computed in ucrm9_geo.py
Ma_maneuver = 0.64
# CL_factor = 1.21 # reference area / true area in ucrm9_geo.py
# height 0
T_maneuver = 288.150
rho_maneuver = 1.22500
gamma = 1.4
R = 287.058
# calculation
sos_maneuver = np.sqrt(gamma*R*T_maneuver)
velocity_maneuver = sos_maneuver * Ma_maneuver
weight = MTOW * 9.8
loadFactor_maneuver = 2.5
CL_manuever = loadFactor_maneuver * weight/(0.5 * rho_maneuver * velocity_maneuver**2 * Area)
print('CL_manuever', CL_manuever)
# --------------------------------
# Compute -1 g dive
# --------------------------------
# parameters
MTOW = 297500 # kg
Area = 410.8 # m^2 reference area computed in ucrm9_geo.py
Ma_dive = 0.64
# CL_factor = 1.21 # reference area / true area in ucrm9_geo.py
# height 0
T_dive = 288.150
rho_dive = 1.22500
gamma = 1.4
R = 287.058
# calculation
sos_dive = np.sqrt(gamma * R * T_dive)
velocity_dive = sos_dive * Ma_dive
weight = MTOW * 9.8
loadFactor_dive = - 1.0
CL_dive = loadFactor_dive * weight/(0.5 * rho_dive * velocity_dive**2 * Area)
print('CL_dive', CL_dive)
# --------------------------------
# Cruise with gust
# --------------------------------
# parameters
MTOW = 297500 # kg
Area = 410.8 # m^2 reference area computed in ucrm9_geo.py
Ma_gust = 0.86
# CL_factor = 1.21 # reference area / true area in ucrm9_geo.py
# height 27300 ft
T_gust = 234.063
rho_gust = 0.505700
gamma = 1.4
R = 287.058
# calculation
sos_gust = np.sqrt(gamma * R * T_gust)
velocity_gust = sos_gust * Ma_gust
weight = MTOW * 9.8
loadFactor_gust = 1.0
CL_gust = loadFactor_gust * weight/(0.5 * rho_gust * velocity_gust**2 * Area)
print('CL_gust', CL_gust)
# ================================
# Aerodynamic analysis
# ================================
# --------------------------------
# cruise
# --------------------------------
T_oper = 216.650
rho_oper = 0.348331
Cl_Ma_pair = [
[0.5, 0.85],
[0.475, 0.85],
[0.525, 0.85],
[0.512, 0.84],
[0.488, 0.86]
]
sum_weight_list = []
for i in range(len(Cl_Ma_pair)):
Ma_loc = Cl_Ma_pair[i][1]
Cl_loc = Cl_Ma_pair[i][0]
# run and save to directory
node, load = getLoad(Cl_loc, Ma_loc, rho_oper, T_oper, CL_factor = CL_factor)
sum_weight_list.append(np.sum(load)/9.8*2)
# --------------------------------
# 2.5 g manuever
# --------------------------------
node_manuever, load_manuever = getLoad(CL_manuever, Ma_maneuver, rho_maneuver, T_maneuver, CL_factor = CL_factor)
# --------------------------------
# -1 g manuever
# --------------------------------
node_dive, load_dive = getLoad(CL_dive, Ma_dive, rho_dive, T_dive, CL_factor = CL_factor)
# --------------------------------
# cruise with gust
# --------------------------------
node_gust, load_gust = getLoad(CL_gust, Ma_gust, rho_gust, T_gust, CL_factor = CL_factor, isGust = True)
# sanity check
print("cruise", sum_weight_list)
print("2.5 g manuever", np.sum(load_manuever)/9.8*2)
print("-1.0 g maneuver", np.sum(load_dive)/9.8*2)
print("gust cruise", np.sum(load_gust)/9.8*2)
print("load_manuever", load_manuever)
# ================================
# transfer the load
# ================================
# get the directory to be interpolated with
import os
rootdir = 'Wings'
dir_list = []
dir_list_total = os.listdir(rootdir)
for i in range(len(dir_list_total)):
dir_loc = dir_list_total[i]
if dir_loc.startswith('W_'):
dir_list.append(rootdir + '/' + dir_loc)
# transfer the load
import sys
sys.path.insert(0, 'transfer')
from transfer import getLoad_new
os.system('mkdir %s' % "./OUT_STRUCT")
os.system('mkdir %s' % "./OUT_STRUCT/Wings")
for i in range(len(Cl_Ma_pair)):
Cl_loc = Cl_Ma_pair[i][0]
Ma_loc = Cl_Ma_pair[i][1]
dir = "OUT_AERO" + "/" + "Cl%.3fMa%.2f" %(Cl_loc, Ma_loc)
node = np.loadtxt(dir+'/'+'node.txt')
load = np.loadtxt(dir+'/'+'load.txt')
# print("np.sum(load)", np.sum(load))
for j in range(len(dir_list)):
dir_loc = dir_list[j]
os.system('mkdir %s' % "./OUT_STRUCT" + "/" + dir_loc)
node_new = np.loadtxt(dir_loc + '/' + 'data_nodes.dat')
load_new = getLoad_new(node, load, node_new)
np.savetxt("./OUT_Struct" + "/" + dir_loc + '/' + "data_forces_Cl%.3fMa%.2f.dat" %(Cl_loc, Ma_loc), load_new)
print("np.sum(load_new)", np.sum(load_new))
# 2.5g
dir = "OUT_AERO" + "/" + "Cl%.3fMa%.2f" %(CL_manuever, Ma_maneuver)
node = np.loadtxt(dir+'/'+'node.txt')
load = np.loadtxt(dir+'/'+'load.txt')
for j in range(len(dir_list)):
dir_loc = dir_list[j]
node_new = np.loadtxt(dir_loc + '/' + 'data_nodes.dat')
load_new = getLoad_new(node, load, node_new)
np.savetxt("./OUT_Struct" + "/" + dir_loc + '/' + "data_forces_Cl%.3fMa%.2f.dat" %(CL_manuever, Ma_maneuver), load_new)
print("np.sum(load_new)", np.sum(load_new))
# -1g
dir = "OUT_AERO" + "/" + "Cl%.3fMa%.2f" %(CL_dive, Ma_dive)
node = np.loadtxt(dir+'/'+'node.txt')
load = np.loadtxt(dir+'/'+'load.txt')
for j in range(len(dir_list)):
dir_loc = dir_list[j]
node_new = np.loadtxt(dir_loc + '/' + 'data_nodes.dat')
load_new = getLoad_new(node, load, node_new)
np.savetxt("./OUT_Struct" + "/" + dir_loc + '/' + "data_forces_Cl%.3fMa%.2f.dat" %(CL_dive, Ma_dive), load_new)
print("np.sum(load_new)", np.sum(load_new))
# gust
dir = "OUT_AERO" + "/" + "Cl%.3fMa%.2f" %(CL_gust, Ma_gust)
node = np.loadtxt(dir+'/'+'node.txt')
load = np.loadtxt(dir+'/'+'load.txt')
for j in range(len(dir_list)):
dir_loc = dir_list[j]
node_new = np.loadtxt(dir_loc + '/' + 'data_nodes.dat')
load_new = getLoad_new(node, load, node_new)
np.savetxt("./OUT_Struct" + "/" + dir_loc + '/' + "data_forces_Cl%.3fMa%.2f.dat" %(CL_gust, Ma_gust), load_new)
print("np.sum(load_new)", np.sum(load_new))