fuel = 56*6.01*0.4535*g
initial_weight = 1111*g
final_weight = initial_weight-fuel
x = np.linspace(final_weight, initial_weight, 100)
y = []
for x_i in x:
y.append(to_integrate(x_i)[0])
range = scipy.integrate.simps(y, x)
return range
# ==============================================================================
# Inputs
# ==============================================================================
altitude = 10000 # ft
air_props = air_properties(altitude, unit='feet')
density = air_props['Density']
# data = pandas.read_csv('performance_grid.csv')
# psi_spars = [0.1, 0.3, 0.6, 0.8]
# c_P = 1.0
# ranges = []
# for i in range(len(data.values)):
# AC = data.values[i,0:4]
# velocity = data.values[i,-4]
# AOA = data.values[i,-5]
# cl= data.values[i,-3]
# cd = data.values[i,-2]
# CL, CD = coefficient_LLT(AC, velocity, AOA)
def aerodynamic_performance(AC, psi_spars, Au_P, Al_P, c_P, deltaz, alpha, H,
V):
morphing_direction = 'forwards'
air_data = air_properties(H, unit='feet')
density = air_data['Density']
dyn_pressure = .5 * density * V**2
# Generate dependent shape coefficients
# try:
Au_C, Al_C, c_C, spar_thicknesses = calculate_dependent_shape_coefficients(
AC, psi_spars, Au_P, Al_P, deltaz, c_P, morphing=morphing_direction)
# print 'Reynolds: ', Reynolds(H, V, c_C)
# Generate aifoil file
airfoil = 'test'
x = create_x(1., distribution='linear', n=300)
y = CST(x, 1., [deltaz / 2., deltaz / 2.], Au=Au_C, Al=Al_C)
# Get strain data
strains, av_strain = calculate_strains(Au_P, Al_P, c_P, Au_C, Al_C, c_C,
deltaz, psi_spars, spar_thicknesses)
intersections = intersect_curves(x, y['l'], x, y['u'])
print(intersections, intersections[0][1:])
if len(intersections[0][1:]) == 0:
# print y
create_input(x, y['u'], y['l'], airfoil, different_x_upper_lower=False)
# Get aerodynamic data
print(airfoil, alpha, Reynolds(H, V, c_C))
Data = find_coefficients(airfoil,
alpha,
Reynolds=Reynolds(H, V, c_C),
iteration=200,
NACA=False,
delete=True,
PANE=True,
GDES=True)
# plot_airfoil(AC, psi_spars, c_P, deltaz, Au_P, Al_P, image = 'save', iteration=counter, dir = airfoil+'_dir')
# filtering data (for now I only care about negative strains
str_output = {
'CL': Data['CL'],
'CD': Data['CD'],
'CM': Data['CM'],
'av_strain': av_strain,
'Au_C': Au_C,
'Al_C': Al_C,
'spars': psi_spars
}
if Data['CM'] == None:
str_output['lift'] = None
str_output['drag'] = None
str_output['moment'] = None
else:
str_output['lift'] = Data['CL'] / dyn_pressure / c_C,
str_output['drag'] = Data['CD'] / dyn_pressure / c_C,
str_output['moment'] = Data['CM'] / dyn_pressure / c_C
for i in range(len(strains)):
str_output['strain_' + str(i)] = strains[i]
# Writing to a text file
# f_worker = open(str(airfoil) + '.txt', 'wb')
# for i in range(len(key_list)):
# if i != len(key_list)-1:
# if key_list[i][:1] == 'Au':
# f_worker.write('%f\t' % str_output[key_list[i][:1]+'_C'][int(key_list[i][-1])])
# else:
# else:
# if key_list[i][:1] == 'Au':
# f_worker.write('%f\n' % str_output[key_list[i][:1]+'_C'][int(key_list[i][-1])])
else:
str_output = {
'CL': 1000,
'CD': None,
'CM': None,
'av_strain': av_strain,
'spars': psi_spars,
'Au_C': Au_C,
'Al_C': Al_C,
'lift': None,
'drag': None,
'moment': None
}
for i in range(len(strains)):
str_output['strain_' + str(i)] = strains[i]
# except:
# str_output = {'CL':None, 'CD':None, 'CM':None, 'av_strain':None,
# 'Au_C':[None]*len(AC), 'Al_C': [None]*len(AC),
# 'lift': None, 'drag': None, 'moment':None,
# 'strains':[None]*(len(AC)-1), 'spars':psi_spars}
return str_output