def setup(self):
indeps = self.add_subsystem('indeps', IndepVarComp(), promotes=['*'])
# load defaults from BPAirfoil
bp = BPAirfoil()
# read last optimization result if available (has to be copied here manually)
if os.path.isfile(INPUT_DIR + '/' + 'airfoil.txt'):
bp.read_parameters_from_file(INPUT_DIR + '/' + 'airfoil.txt')
indeps.add_output('r_le', bp.r_le)
indeps.add_output('beta_te', bp.beta_te)
indeps.add_output('x_t', bp.x_t)
indeps.add_output('gamma_le', bp.gamma_le)
indeps.add_output('x_c', bp.x_c)
indeps.add_output('y_c', bp.y_c)
indeps.add_output('alpha_te', bp.alpha_te)
indeps.add_output('b_8', bp.b_8)
indeps.add_output('b_15', bp.b_15)
indeps.add_output('b_0', bp.b_0)
indeps.add_output('b_2', bp.b_2)
indeps.add_output('b_17', bp.b_17)
indeps.add_output('offsetFront', .1)
indeps.add_output('angle', 0.)
indeps.add_output('bz_y_t', bp.y_t)
cycle = self.add_subsystem('cycle', Group())
cyc1 = cycle.add_subsystem('cyc1', ProfileFitting())
# Nonlinear Block Gauss Seidel is a gradient free solver
cycle.nonlinear_solver = NewtonSolver() #NonlinearBlockGS()
cycle.nonlinear_solver.options['maxiter'] = 200
cycle.nonlinear_solver.options['atol'] = 1e-6
cycle.nonlinear_solver.options['solve_subsystems'] = True
cycle.linear_solver = ScipyKrylov()
self.add_subsystem('airfoil_cfd', AirfoilCFD())
self.connect('r_le', 'airfoil_cfd.r_le')
self.connect('beta_te', 'airfoil_cfd.beta_te')
self.connect('x_t', 'airfoil_cfd.x_t')
self.connect('gamma_le', 'airfoil_cfd.gamma_le')
self.connect('x_c', 'airfoil_cfd.x_c')
self.connect('y_c', 'airfoil_cfd.y_c')
self.connect('alpha_te', 'airfoil_cfd.alpha_te')
self.connect('b_8', 'airfoil_cfd.b_8')
self.connect('b_15', 'airfoil_cfd.b_15')
self.connect('b_0', 'airfoil_cfd.b_0')
self.connect('b_2', 'airfoil_cfd.b_2')
self.connect('b_17', 'airfoil_cfd.b_17')
self.connect('offsetFront', ['cycle.cyc1.offsetFront', 'airfoil_cfd.offsetFront'])
self.connect('angle', ['cycle.cyc1.angle', 'airfoil_cfd.angle'])
self.connect('bz_y_t', ['cycle.cyc1.bz_y_t', 'airfoil_cfd.y_t'])
self.connect('cycle.cyc1.height', 'airfoil_cfd.cabin_height')
def setup(self):
######################
### needed Objects ###
self.bzFoil = BPAirfoil()
self.air = Airfoil(None)
#####################
### openMDAO init ###
### INPUTS
self.add_input('r_le', val=-0.05, desc='nose radius')
self.add_input('beta_te',
val=0.1,
desc='thickness angle trailing edge')
#self.add_input('dz_te', val=0., desc='thickness trailing edge')
self.add_input('x_t', val=0.3, desc='dickenruecklage')
#self.add_input('y_t', val=0.1, desc='max thickness')
self.add_input('gamma_le', val=0.5, desc='camber angle leading edge')
self.add_input('x_c', val=0.5, desc='woelbungsruecklage')
self.add_input('y_c', val=0.1, desc='max camber')
self.add_input('alpha_te', val=-0.1, desc='camber angle trailing edge')
#self.add_input('z_te', val=0., desc='camber trailing edge')
# bezier parameters
self.add_input('b_8', val=0.05, desc='')
self.add_input('b_15', val=0.75, desc='')
self.add_input('b_0', val=0.1, desc='')
self.add_input('b_2', val=0.25, desc='')
self.add_input('b_17', val=0.9, desc='')
# just for plotin
#self.add_input('offsetFront', val=0.1, desc='...')
#self.add_input('angle', val=.0, desc='...')
#self.add_input('cabin_height', val=.0, desc='...')
### OUTPUTS
self.add_output('c_d', val=.2)
self.add_output('c_l', val=.2)
self.add_output('c_m', val=.2)
self.add_output('y_t', val=0.1, desc='max thickness')
self.add_output('cabin_height', val=cabinHeigth)
self.add_output('angle', val=.0, desc='...')
self.add_output('offsetFront', val=0.1, desc='...')
self.declare_partials('*', '*', method='fd')
self.executionCounter = 0
self.prevAngle = -0.239
self.prevOffsetFront = 0.117
def setup(self):
self.bzFoil = BPAirfoil()
self.air = Airfoil(None)
#####################
### openMDAO init ###
### INPUTS
self.add_input('offsetFront', val=0.1, desc='...')
#self.add_input('length', val=1.0, desc='...')
self.add_input('angle', val=1.0, desc='...')
self.add_input('bz_y_t', val=.2, desc='...')
### OUTPUTS
self.add_output('height', val=0.0)
self.add_output('heightLoss', val=0.0)
self.declare_partials('*', '*', method='fd')
self.executionCounter = 0
class ProfileFitting(ExplicitComponent):
def setup(self):
self.bzFoil = BPAirfoil()
self.air = Airfoil(None)
#####################
### openMDAO init ###
### INPUTS
self.add_input('offsetFront', val=0.1, desc='...')
#self.add_input('length', val=1.0, desc='...')
self.add_input('angle', val=1.0, desc='...')
self.add_input('bz_y_t', val=.2, desc='...')
### OUTPUTS
self.add_output('height', val=0.0)
self.add_output('heightLoss', val=0.0)
self.declare_partials('*', '*', method='fd')
self.executionCounter = 0
def fit_cabin(self, xFront, angle):
top, buttom = self.bzFoil.get_cooridnates_top_buttom(500)
if self.bzFoil.valid == False:
return False, False
xBack = xFront + cabinLength # inputs['length']
self.air.set_coordinates(top, buttom)
self.air.rotate(angle)
yMinButtom = max(self.air.get_buttom_y(xFront), self.air.get_buttom_y(xBack))
yMaxTop = min(self.air.get_top_y(xFront), self.air.get_top_y(xBack))
maxHeight = max(self.air.get_top_y(xFront) - self.air.get_buttom_y(xFront), self.air.get_top_y(xBack) - self.air.get_buttom_y(xBack))
height = yMaxTop - yMinButtom
return height, maxHeight
def compute(self, inputs, outputs):
self.bzFoil = globBzFoil
self.bzFoil.y_t = inputs['bz_y_t']
# check how high the cabin can be
height, maxHeight = self.fit_cabin(inputs['offsetFront'], inputs['angle'])
if not self.bzFoil.valid:
print('ANALYSIS ERROR !')
outputs['height'] = 1.
outputs['heightLoss'] = 1.
else:
outputs['height'] = height #yMaxTop- yMinButtom
outputs['heightLoss'] = maxHeight - height
self.executionCounter += 1
print(str(self.executionCounter) + '\t' + str(outputs['heightLoss']) + '\t' + str(inputs['bz_y_t']) + '\t' + str(outputs['height']))
import os
from airfoil.Airfoil import Airfoil
from airfoil.BPAirfoil import BPAirfoil
from openmdao.api import Problem, ScipyOptimizeDriver, IndepVarComp, ExplicitComponent
import matplotlib.pyplot as plt
from openmdao.core.problem import Problem
from openmdao.core.indepvarcomp import IndepVarComp
#import libaries.readInput as readInputs
#from libaries.readInput import ParamValue
#value = readInputs.readInputFile()
bzFoil = BPAirfoil()
if os.path.isfile('../dataIn/airfoil.txt'):
bzFoil.read_parameters_from_file('../dataIn/airfoil.txt')
air = Airfoil(None)
top, buttom = bzFoil.get_cooridnates_top_buttom(500)
if bzFoil.valid == False:
print('ERROR: invalid bzArifoil')
air.set_coordinates(top, buttom)
cabinLength = 0.55
cabinHeigth = 0.14
class ProfileFitting(ExplicitComponent):
class AirfoilCFD(ExplicitComponent):
def setup(self):
######################
### needed Objects ###
self.bzFoil = BPAirfoil()
#####################
### openMDAO init ###
### INPUTS
self.add_input('r_le', val=-0.05, desc='nose radius')
self.add_input('beta_te', val=0.1, desc='thickness angle trailing edge')
#self.add_input('dz_te', val=0., desc='thickness trailing edge')
self.add_input('x_t', val=0.3, desc='dickenruecklage')
self.add_input('y_t', val=0.1, desc='max thickness')
self.add_input('gamma_le', val=0.5, desc='camber angle leading edge')
self.add_input('x_c', val=0.5, desc='woelbungsruecklage')
self.add_input('y_c', val=0.1, desc='max camber')
self.add_input('alpha_te', val=-0.1, desc='camber angle trailing edge')
self.add_input('z_te', val=0., desc='camber trailing edge')
# bezier parameters
self.add_input('b_8', val=0.05, desc='')
self.add_input('b_15', val=0.75, desc='')
self.add_input('b_0', val=0.1, desc='')
self.add_input('b_2', val=0.25, desc='')
self.add_input('b_17', val=0.9, desc='')
# just for plotin
self.add_input('offsetFront', val=0.1, desc='...')
self.add_input('angle', val=.0, desc='...')
self.add_input('cabin_height', val=.0, desc='...')
### OUTPUTS
self.add_output('c_d', val=.2)
self.add_output('c_l', val=.2)
self.add_output('c_m', val=.2)
self.declare_partials('*', '*', method='fd')
self.executionCounter = 0
def compute(self, inputs, outputs):
error = False
self.bzFoil.r_le = inputs['r_le']
self.bzFoil.beta_te = inputs['beta_te']
#self.bzFoil.dz_te = inputs['dz_te']
self.bzFoil.x_t = inputs['x_t']
self.bzFoil.y_t = inputs['y_t']
self.bzFoil.gamma_le = inputs['gamma_le']
self.bzFoil.x_c = inputs['x_c']
self.bzFoil.y_c = inputs['y_c']
self.bzFoil.alpha_te = inputs['alpha_te']
self.bzFoil.z_te = inputs['z_te']
self.bzFoil.b_8 = inputs['b_8']
self.bzFoil.b_15 = inputs['b_15']
self.bzFoil.b_0 = inputs['b_0']
self.bzFoil.b_2 = inputs['b_2']
self.bzFoil.b_17 = inputs['b_17']
projectName = PROJECT_NAME_PREFIX + '_%09d' % self.executionCounter
cfd = CFDrun(projectName)
airFoilCoords = self.bzFoil.generate_airfoil(500,
show_plot=False,
save_plot_path=WORKING_DIR+'/'+projectName+'/airfoil.png',
param_dump_file=WORKING_DIR+'/'+projectName+'/airfoil.txt')
self.bzFoil.plot_airfoil_with_cabin(inputs['offsetFront'],
cabinLength,
inputs['cabin_height'],
inputs['angle'],
show_plot=False,
save_plot_path=WORKING_DIR+'/'+projectName+'/airfoil_cabin.png')
if not self.bzFoil.valid:
#raise AnalysisError('AirfoilCFD: invalid BPAirfoil')
print('ERROR: AirfoilCFD, invalid BPAirfoil')
error = True
else:
top, buttom = self.bzFoil.get_cooridnates_top_buttom(500)
#self.air.set_coordinates(top, buttom)
cfd.set_airfoul_coords(top, buttom)
cfd.c2d.pointsInNormalDir = 80
cfd.c2d.pointNrAirfoilSurface = 200
cfd.c2d.reynoldsNum = REYNOLD
cfd.construct2d_generate_mesh(scale=SCALE, plot=False)
cfd.su2_fix_mesh()
cfd.su2_solve(config)
#totalCL, totalCD, totalCM, totalE = cfd.su2_parse_results()
results = cfd.su2_parse_iteration_result()
cfd.clean_up()
if float(results['CD']) <= 0. or float(results['CD']) > 100.:
#raise AnalysisError('AirfoilCFD: c_d is out of range (cfd failed)')
print('ERROR: AirfoilCFD, c_d is out of range (cfd failed)')
error = True
outputs['c_d'] = results['CD']
outputs['c_l'] = results['CL']
outputs['c_m'] = results['CMz']
print('c_l= ' + str(outputs['c_l']))
print('c_d= ' + str(outputs['c_d']))
print('c_m= ' + str(outputs['c_m']))
print('c_l/c_d= ' + str(results['CL/CD']))
print('cfdIterations= ' + str(results['Iteration']))
write_to_log(str(self.executionCounter) + ','
+ datetime.now().strftime('%H:%M:%S') + ','
+ str(outputs['c_l']) + ','
+ str(outputs['c_d']) + ','
+ str(outputs['c_m']) + ','
+ str(results['CL/CD']) + ','
+ str(results['Iteration']) + ','
+ str(inputs['cabin_height']) + ','
+ str(inputs['offsetFront']) + ','
+ str(inputs['angle']) + ','
+ str(inputs['r_le']) + ','
+ str(inputs['beta_te']) + ','
+ str(inputs['x_t']) + ','
+ str(inputs['y_t']) + ','
+ str(inputs['gamma_le']) + ','
+ str(inputs['x_c']) + ','
+ str(inputs['y_c']) + ','
+ str(inputs['alpha_te']) + ','
+ str(inputs['z_te']) + ','
+ str(inputs['b_8']) + ','
+ str(inputs['b_15']) + ','
+ str(inputs['b_0']) + ','
+ str(inputs['b_17']) + ','
+ str(inputs['b_2']))
#workaround since raising an error seems to crash the optimization
if error:
outputs['c_d'] = 999.
outputs['c_l'] = 0.
outputs['c_m'] = 0.
self.executionCounter += 1
def runOpenMdao():
prob = Problem()
#first guesses here
indeps = prob.model.add_subsystem('indeps', IndepVarComp(), promotes=['*'])
#indeps.add_output('length', .5)
#indeps.add_output('height', .1)
indeps.add_output('offsetFront', .11)
indeps.add_output('angle', 0.)
# load defaults from BPAirfoil
bp = BPAirfoil()
# read last optimization result if available (has to be copied here manually)
if os.path.isfile(INPUT_DIR+'/'+'airfoil.txt'):
bp.read_parameters_from_file(INPUT_DIR+'/'+'airfoil.txt')
indeps.add_output('r_le', bp.r_le)
indeps.add_output('beta_te', bp.beta_te)
#indeps.add_output('dz_te', bp.dz_te) # we want a sharp trailing edge
indeps.add_output('x_t', bp.x_t)
indeps.add_output('y_t', bp.y_t)
indeps.add_output('gamma_le', bp.gamma_le)
indeps.add_output('x_c', bp.x_c)
indeps.add_output('y_c', bp.y_c)
indeps.add_output('alpha_te', bp.alpha_te)
indeps.add_output('z_te', bp.z_te)
indeps.add_output('b_8', bp.b_8)
indeps.add_output('b_15', bp.b_15)
indeps.add_output('b_0', bp.b_0)
indeps.add_output('b_2', bp.b_2)
indeps.add_output('b_17', bp.b_17)
prob.model.add_subsystem('airfoil_cfd', AirfoilCFD())
prob.model.add_subsystem('cabin_fitter', CabinFitting())
#prob.model.connect('length', 'cabin_fitter.length')
prob.model.connect('offsetFront', ['cabin_fitter.offsetFront', 'airfoil_cfd.offsetFront'])
prob.model.connect('angle', ['cabin_fitter.angle', 'airfoil_cfd.angle'])
prob.model.connect('cabin_fitter.cabin_height', 'airfoil_cfd.cabin_height')
prob.model.connect('r_le', ['airfoil_cfd.r_le', 'cabin_fitter.r_le'])
prob.model.connect('beta_te', ['airfoil_cfd.beta_te', 'cabin_fitter.beta_te'])
#prob.model.connect('dz_te', ['airfoil_cfd.dz_te', 'cabin_fitter.dz_te'])
prob.model.connect('x_t', ['airfoil_cfd.x_t', 'cabin_fitter.x_t'])
prob.model.connect('y_t', ['airfoil_cfd.y_t', 'cabin_fitter.y_t'])
prob.model.connect('gamma_le', ['airfoil_cfd.gamma_le', 'cabin_fitter.gamma_le'])
prob.model.connect('x_c', ['airfoil_cfd.x_c', 'cabin_fitter.x_c'])
prob.model.connect('y_c', ['airfoil_cfd.y_c', 'cabin_fitter.y_c'])
prob.model.connect('alpha_te', ['airfoil_cfd.alpha_te', 'cabin_fitter.alpha_te'])
prob.model.connect('z_te', ['airfoil_cfd.z_te', 'cabin_fitter.z_te'])
prob.model.connect('b_8', ['airfoil_cfd.b_8', 'cabin_fitter.b_8'])
prob.model.connect('b_15', ['airfoil_cfd.b_15', 'cabin_fitter.b_15'])
prob.model.connect('b_0', ['airfoil_cfd.b_0', 'cabin_fitter.b_0'])
prob.model.connect('b_2', ['airfoil_cfd.b_2', 'cabin_fitter.b_2'])
prob.model.connect('b_17', ['airfoil_cfd.b_17', 'cabin_fitter.b_17'])
# setup the optimization
prob.driver = ScipyOptimizeDriver()
prob.driver.options['optimizer'] = 'SLSQP'
prob.driver.options['tol'] = 1e-9
prob.driver.options['maxiter'] = 100000
# setup recorder
recorder = SqliteRecorder(WORKING_DIR + '/openMdaoLog.sql')
prob.driver.add_recorder(recorder)
prob.driver.recording_options['record_desvars'] = True
prob.driver.recording_options['record_responses'] = True
prob.driver.recording_options['record_objectives'] = True
prob.driver.recording_options['record_constraints'] = True
#limits and constraints
#prob.model.add_design_var('length', lower=0.4, upper=0.5)
#lowerPro = 0.9
#upperPro = 1.1
prob.model.add_design_var('r_le', upper=0.)#, lower=-1*bp.y_t, upper=0)
prob.model.add_design_var('beta_te')#, lower=bp.beta_te*lowerPro, upper=bp.beta_te*upperPro)
#ToDo: dz_te constant to 0, no thickness at trailing edge
#prob.model.add_design_var('dz_te', lower=0., upper=0.)
prob.model.add_design_var('x_t', lower=0.)#, lower=0.25, upper=0.5)
prob.model.add_design_var('y_t')#, lower=0.075, upper=0.09)
prob.model.add_design_var('gamma_le')#, lower=bp.gamma_le*lowerPro, upper=bp.gamma_le*upperPro)
prob.model.add_design_var('x_c')#, lower=bp.x_c*lowerPro, upper=bp.x_c*upperPro)
prob.model.add_design_var('y_c')#, lower=bp.y_c*lowerPro, upper=bp.y_c*upperPro)
prob.model.add_design_var('alpha_te')#, lower=bp.alpha_te*upperPro, upper=bp.alpha_te*lowerPro)
prob.model.add_design_var('z_te')#, lower=0., upper=0.)
prob.model.add_design_var('b_8')#, lower=bp.b_8*lowerPro, upper=bp.b_8*upperPro)
prob.model.add_design_var('b_15')#, lower=bp.b_15*lowerPro, upper=bp.b_15*upperPro)
prob.model.add_design_var('b_0')#, lower=bp.b_0*lowerPro, upper=bp.b_0*upperPro)
prob.model.add_design_var('b_2')#, lower=bp.b_2*lowerPro, upper=bp.b_2*upperPro)
prob.model.add_design_var('b_17')#, lower=bp.b_17*lowerPro, upper=bp.b_17*upperPro)
prob.model.add_design_var('offsetFront', lower=0.0, upper=.5)
prob.model.add_design_var('angle', lower=-5, upper=5)
prob.model.add_objective('airfoil_cfd.c_d', scaler=1)
prob.model.add_constraint('cabin_fitter.cabin_height', lower=cabinHeigth * 0.99, upper=cabinHeigth*1.05)
prob.model.add_constraint('airfoil_cfd.c_l', lower=0.145, upper=.155)
prob.model.add_constraint('airfoil_cfd.c_m', lower=-0.05, upper=99.)
write_to_log('iterations,time,c_l,c_d,c_m,CL/CD,cfdIterations,cabin_height,offsetFront,angle,r_le,beta_te,x_t,y_t,gamma_le,x_c,y_c,alpha_te,z_te,b_8,b_15,b_0,b_17,b_2]))')
prob.setup()
prob.set_solver_print(level=0)
prob.model.approx_totals()
prob.run_driver()
print('done')
print('cabin frontOddset: ' + str(prob['offsetFront']))
print('cabin angle: ' + str(-1. * prob['angle']) + ' deg')
print('c_l= ' + str(prob['airfoil_cfd.c_l']))
print('c_d= ' + str(prob['airfoil_cfd.c_d']))
print('c_m= ' + str(prob['airfoil_cfd.c_m']))
print('execution counts cabin fitter: ' + str(prob.model.cabin_fitter.executionCounter))
print('execution counts airfoil cfd: ' + str(prob.model.airfoil_cfd.executionCounter))
class CabinFitting(ExplicitComponent):
def setup(self):
######################
### needed Objects ###
self.bzFoil = BPAirfoil()
self.air = Airfoil(None)
#####################
### openMDAO init ###
### INPUTS
self.add_input('r_le', val=-0.05, desc='nose radius')
self.add_input('beta_te', val=0.1, desc='thickness angle trailing edge')
#self.add_input('dz_te', val=0., desc='thickness trailing edge')
self.add_input('x_t', val=0.3, desc='dickenruecklage')
self.add_input('y_t', val=0.1, desc='max thickness')
self.add_input('gamma_le', val=0.5, desc='camber angle leading edge')
self.add_input('x_c', val=0.5, desc='woelbungsruecklage')
self.add_input('y_c', val=0.1, desc='max camber')
self.add_input('alpha_te', val=-0.1, desc='camber angle trailing edge')
self.add_input('z_te', val=0., desc='camber trailing edge')
# bezier parameters
self.add_input('b_8', val=0.05, desc='')
self.add_input('b_15', val=0.75, desc='')
self.add_input('b_0', val=0.1, desc='')
self.add_input('b_2', val=0.25, desc='')
self.add_input('b_17', val=0.9, desc='')
self.add_input('offsetFront', val=0.1, desc='...')
#self.add_input('length', val=.5, desc='...')
self.add_input('angle', val=.0, desc='...')
### OUTPUTS
#self.add_output('height', val=0.0)
self.add_output('cabin_height', val=cabinHeigth)
self.declare_partials('*', '*', method='fd')
self.executionCounter = 0
def compute(self, inputs, outputs):
self.bzFoil.r_le = inputs['r_le']
self.bzFoil.beta_te = inputs['beta_te']
#self.bzFoil.dz_te = inputs['dz_te']
self.bzFoil.x_t = inputs['x_t']
self.bzFoil.y_t = inputs['y_t']
self.bzFoil.gamma_le = inputs['gamma_le']
self.bzFoil.x_c = inputs['x_c']
self.bzFoil.y_c = inputs['y_c']
self.bzFoil.alpha_te = inputs['alpha_te']
self.bzFoil.z_te = inputs['z_te']
self.bzFoil.b_8 = inputs['b_8']
self.bzFoil.b_15 = inputs['b_15']
self.bzFoil.b_0 = inputs['b_0']
self.bzFoil.b_2 = inputs['b_2']
self.bzFoil.b_17 = inputs['b_17']
xFront = inputs['offsetFront']
xBack = xFront + cabinLength #inputs['length']
angle = inputs['angle']
top, buttom = self.bzFoil.get_cooridnates_top_buttom(500, show_plot=False)
self.air.set_coordinates(top, buttom)
self.air.rotate(angle)
yMinButtom = max(self.air.get_buttom_y(xFront), self.air.get_buttom_y(xBack))
yMaxTop = min(self.air.get_top_y(xFront), self.air.get_top_y(xBack))
height = yMaxTop - yMinButtom
"""
iterCounter = 0
while(abs(height - cabinHeigth) > 1e-6):
self.bzFoil.y_t += cabinHeigth - height
top, buttom = self.bzFoil.get_cooridnates_top_buttom(500)
self.air.set_coordinates(top, buttom)
self.air.rotate(angle)
yMinButtom = max(self.air.get_buttom_y(xFront), self.air.get_buttom_y(xBack))
yMaxTop = min(self.air.get_top_y(xFront), self.air.get_top_y(xBack))
height = yMaxTop - yMinButtom
iterCounter += 1
"""
if not self.bzFoil.valid:
print('ERROR: CabinFitting, invalid BPAirfoil')
print('But we let AirfoilCFD handle this')
self.bzFoil.save_parameters_to_file(WORKING_DIR + '/bz_error_' + datetime.now().strftime('%Y-%m-%d_%H_%M_%S') + '.txt')
#raise AnalysisError('CabinFitting: invalid BPAirfoil')
#workaround to tell openMDAO that this is bad
outputs['cabin_height'] = 0.
else:
#yMinButtom = max(self.air.get_buttom_y(xFront), self.air.get_buttom_y(xBack))
#yMaxTop = min(self.air.get_top_y(xFront), self.air.get_top_y(xBack))
#outputs['height'] = yMaxTop - yMinButtom
#print('cabin fitting needed ' + str(iterCounter) + ' iterations')
print('cabinHeight= ' + str(height))
outputs['cabin_height'] = height
print('new cabin_height= ' + str(outputs['cabin_height']))
self.executionCounter += 1
from cfd.CFDrun import CFDrun
from airfoil.BPAirfoil import BPAirfoil
from airfoil.Airfoil import Airfoil
from constants import *
import optimization.cabinFitOptimizerV2 as cabin
####################################
### setup
####################################
#cfd = CFDrun('export', used_cores=SU2_USED_CORES)
#cfd.load_airfoil_from_file(INPUT_DIR + '/vfw-va2.dat')
# load defaults from BPAirfoil
bp = BPAirfoil()
# read last optimization result if available (has to be copied here manually)
if os.path.isfile(INPUT_DIR + '/' + 'airfoil.txt'):
bp.read_parameters_from_file(INPUT_DIR + '/' + 'airfoil.txt')
else:
print('error, no default airfoil.txt')
sys.exit(1)
##################################
### naca Test ca, cd over mach ###
print('export data to m-file')
filePath = WORKING_DIR + '/' + 'dataAirfoilOptimizer.m'
outputF = open(filePath, 'w')
outputF.write(
class AirfoilCFD(ExplicitComponent):
def setup(self):
######################
### needed Objects ###
self.bzFoil = BPAirfoil()
self.air = Airfoil(None)
#####################
### openMDAO init ###
### INPUTS
self.add_input('r_le', val=-0.05, desc='nose radius')
self.add_input('beta_te', val=0.1, desc='thickness angle trailing edge')
self.add_input('x_t', val=0.3, desc='dickenruecklage')
self.add_input('y_t', val=0.1, desc='max thickness')
self.add_input('gamma_le', val=0.5, desc='camber angle leading edge')
self.add_input('x_c', val=0.5, desc='woelbungsruecklage')
self.add_input('y_c', val=0.1, desc='max camber')
self.add_input('alpha_te', val=-0.1, desc='camber angle trailing edge')
#self.add_input('z_te', val=0., desc='camber trailing edge')
# bezier parameters
self.add_input('b_8', val=0.05, desc='')
self.add_input('b_15', val=0.75, desc='')
self.add_input('b_0', val=0.1, desc='')
self.add_input('b_2', val=0.25, desc='')
self.add_input('b_17', val=0.9, desc='')
###only for visualiziation
self.add_input('offsetFront', val=0.1, desc='...')
self.add_input('cabin_height', val=1.0, desc='...')
self.add_input('angle', val=1.0, desc='...')
### OUTPUTS
self.add_output('c_d', val=.2)
self.add_output('c_l', val=.2)
self.add_output('c_m', val=.2)
#self.add_output('y_t', val=0.1, desc='max thickness')
#self.add_output('cabin_height', val=cabinHeigth)
#self.add_output('angle', val=0.)
#self.add_output('offsetFront', val=.1)
self.declare_partials('*', '*', method='fd')
self.executionCounter = 0
"""
def fit_cabin(self, xFront, angle):
top, buttom = self.bzFoil.get_cooridnates_top_buttom(500)
if self.bzFoil.valid == False:
return False
xBack = xFront + cabinLength # inputs['length']
self.air.set_coordinates(top, buttom)
self.air.rotate(angle)
yMinButtom = max(self.air.get_buttom_y(xFront), self.air.get_buttom_y(xBack))
yMaxTop = min(self.air.get_top_y(xFront), self.air.get_top_y(xBack))
height = yMaxTop - yMinButtom
return height
#outputs['cabin_height'] = height
"""
def compute(self, inputs, outputs):
error = False
self.bzFoil.r_le = inputs['r_le']
self.bzFoil.beta_te = inputs['beta_te']
self.bzFoil.x_t = inputs['x_t']
self.bzFoil.y_t = inputs['y_t']
self.bzFoil.gamma_le = inputs['gamma_le']
self.bzFoil.x_c = inputs['x_c']
self.bzFoil.y_c = inputs['y_c']
self.bzFoil.alpha_te = inputs['alpha_te']
#self.bzFoil.z_te = inputs['z_te']
self.bzFoil.b_8 = inputs['b_8']
self.bzFoil.b_15 = inputs['b_15']
self.bzFoil.b_0 = inputs['b_0']
self.bzFoil.b_2 = inputs['b_2']
self.bzFoil.b_17 = inputs['b_17']
projectName = PROJECT_NAME_PREFIX + '_%09d' % self.executionCounter
cfd = CFDrun(projectName)
airFoilCoords = self.bzFoil.generate_airfoil(500,
show_plot=False,
save_plot_path=WORKING_DIR+'/'+projectName+'/airfoil.png',
param_dump_file=WORKING_DIR+'/'+projectName+'/airfoil.txt')
# check if bz is valid
if self.bzFoil.valid:
print('valid bz')
### use cabin fit optimization to find y_t
#cabinFit.cabinHeigth = cabinHeigth
#cabinFit.cabinLength = cabinLength
#cabinFit.bzFoil = self.bzFoil
#y_t, height, angle, offsetFront = cabinFit.run_cabin_opti(show_plot=False)
#self.bzFoil.y_t = y_t
#outputs['cabin_height'] = height
#outputs['y_t'] = y_t
#outputs['angle'] = angle
#outputs['offsetFront'] = offsetFront
#print('new cabin_height= ' + str(outputs['cabin_height']))
if not self.bzFoil.valid:
#raise AnalysisError('AirfoilCFD: invalid BPAirfoil')
print('ERROR: AirfoilCFD, invalid BPAirfoil')
self.bzFoil.save_parameters_to_file(
WORKING_DIR + '/bz_error_' + datetime.now().strftime('%Y-%m-%d_%H_%M_%S') + '.txt')
error = True
else:
self.bzFoil.plot_airfoil_with_cabin(inputs['offsetFront'],
cabinLength,
inputs['cabin_height'],
inputs['angle'],
show_plot=False,
save_plot_path=WORKING_DIR + '/' + projectName + '/airfoil_cabin.png')
### now we do cfd
top, buttom = self.bzFoil.get_cooridnates_top_buttom(500)
cfd.set_airfoul_coords(top, buttom)
cfd.c2d.pointsInNormalDir = 80
cfd.c2d.pointNrAirfoilSurface = 200
cfd.c2d.reynoldsNum = REYNOLD
cfd.construct2d_generate_mesh(scale=SCALE, plot=False)
cfd.su2_fix_mesh()
cfd.su2_solve(config)
results = cfd.su2_parse_iteration_result()
cfd.clean_up()
if float(results['CD']) <= 0. or float(results['CD']) > 100.:
#raise AnalysisError('AirfoilCFD: c_d is out of range (cfd failed)')
print('ERROR: AirfoilCFD, c_d is out of range (cfd failed)')
error = True
outputs['c_d'] = results['CD']
outputs['c_l'] = results['CL']
outputs['c_m'] = results['CMz']
print('c_l= ' + str(outputs['c_l']))
print('c_d= ' + str(outputs['c_d']))
print('c_m= ' + str(outputs['c_m']))
print('c_l/c_d= ' + str(results['CL/CD']))
print('cfdIterations= ' + str(results['Iteration']))
write_to_log(str(self.executionCounter) + ','
+ datetime.now().strftime('%H:%M:%S') + ','
+ str(outputs['c_l']) + ','
+ str(outputs['c_d']) + ','
+ str(outputs['c_m']) + ','
+ str(results['CL/CD']) + ','
+ str(results['Iteration']) + ','
+ str(inputs['cabin_height']) + ','
+ str(inputs['offsetFront']) + ','
+ str(inputs['angle']) + ','
+ str(inputs['r_le']) + ','
+ str(inputs['beta_te']) + ','
+ str(inputs['x_t']) + ','
+ str(inputs['y_t']) + ','
+ str(inputs['gamma_le']) + ','
+ str(inputs['x_c']) + ','
+ str(inputs['y_c']) + ','
+ str(inputs['alpha_te']) + ','
+ str(self.bzFoil.z_te) + ','#+ str(inputs['z_te']) + ','
+ str(inputs['b_8']) + ','
+ str(inputs['b_15']) + ','
+ str(inputs['b_0']) + ','
+ str(inputs['b_17']) + ','
+ str(inputs['b_2']))
globBzFoil = self.bzFoil
#workaround since raising an error seems to crash the optimization
if error:
outputs['c_d'] = 999.
outputs['c_l'] = 0.
outputs['c_m'] = 0.
self.executionCounter += 1
config['MGCYCLE'] = 'V_CYCLE'
config['MG_DAMP_RESTRICTION'] = str(.45)
config['MG_DAMP_PROLONGATION'] = str(.45)
#config['CFL_ADAPT'] = 'YES'
#config['CFL_ADAPT_PARAM'] = '( 1.5, 0.5, 1.0, 50.0 )'
config['TIME_DISCRE_FLOW'] = 'EULER_IMPLICIT'
config['CONV_NUM_METHOD_FLOW'] = 'JST'
config['RELAXATION_FACTOR_FLOW'] = str(1.)
config['RELAXATION_FACTOR_TURB'] = str(1.)
cabinLength = 0.55
cabinHeigth = 0.14
globBzFoil = BPAirfoil()
class AirfoilCFD(ExplicitComponent):
def setup(self):
######################
### needed Objects ###
self.bzFoil = BPAirfoil()
self.air = Airfoil(None)
#####################
### openMDAO init ###
### INPUTS
self.add_input('r_le', val=-0.05, desc='nose radius')
def runOpenMdao():
prob = Problem()
#first guesses here
indeps = prob.model.add_subsystem('indeps', IndepVarComp(), promotes=['*'])
# load defaults from BPAirfoil
bp = BPAirfoil()
# read last optimization result if available (has to be copied here manually)
if os.path.isfile(INPUT_DIR + '/' + 'airfoil.txt'):
bp.read_parameters_from_file(INPUT_DIR + '/' + 'airfoil.txt')
indeps.add_output('r_le', bp.r_le)
indeps.add_output('beta_te', bp.beta_te)
indeps.add_output('x_t', bp.x_t)
indeps.add_output('gamma_le', bp.gamma_le)
indeps.add_output('x_c', bp.x_c)
indeps.add_output('y_c', bp.y_c)
indeps.add_output('alpha_te', bp.alpha_te)
#indeps.add_output('z_te', bp.z_te)
indeps.add_output('b_8', bp.b_8)
indeps.add_output('b_15', bp.b_15)
indeps.add_output('b_0', bp.b_0)
indeps.add_output('b_2', bp.b_2)
indeps.add_output('b_17', bp.b_17)
prob.model.add_subsystem('airfoil_cfd', AirfoilCFD())
prob.model.connect('r_le', 'airfoil_cfd.r_le')
prob.model.connect('beta_te', 'airfoil_cfd.beta_te')
prob.model.connect('x_t', 'airfoil_cfd.x_t')
prob.model.connect('gamma_le', 'airfoil_cfd.gamma_le')
prob.model.connect('x_c', 'airfoil_cfd.x_c')
prob.model.connect('y_c', 'airfoil_cfd.y_c')
prob.model.connect('alpha_te', 'airfoil_cfd.alpha_te')
#prob.model.connect('z_te', 'airfoil_cfd.z_te')
prob.model.connect('b_8', 'airfoil_cfd.b_8')
prob.model.connect('b_15', 'airfoil_cfd.b_15')
prob.model.connect('b_0', 'airfoil_cfd.b_0')
prob.model.connect('b_2', 'airfoil_cfd.b_2')
prob.model.connect('b_17', 'airfoil_cfd.b_17')
# setup the optimization
prob.driver = ScipyOptimizeDriver()
#'Nelder-Mead', 'Powell', 'CG', 'BFGS', 'Newton-CG', 'L-BFGS-B', 'TNC', 'COBYLA', 'SLSQP']
prob.driver.options['optimizer'] = 'COBYLA'
prob.driver.options['tol'] = 1e-6
prob.driver.options['maxiter'] = 100000
# setup recorder
recorder = SqliteRecorder(WORKING_DIR + '/openMdaoLog.sql')
prob.driver.add_recorder(recorder)
prob.driver.recording_options['record_desvars'] = True
prob.driver.recording_options['record_responses'] = True
prob.driver.recording_options['record_objectives'] = True
prob.driver.recording_options['record_constraints'] = True
#limits and constraints
lowerPro = 0.9
upperPro = 1.1
prob.model.add_design_var('r_le', lower=-0.1, upper=-0.015)
prob.model.add_design_var('beta_te', lower=0, upper=0.3)
#prob.model.add_design_var('dz_te', lower=0., upper=0.)
prob.model.add_design_var('x_t', lower=0.25, upper=0.4)
#prob.model.add_design_var('y_t')#, lower=0.075, upper=0.09)
prob.model.add_design_var('gamma_le', lower=0.05, upper=0.4)
prob.model.add_design_var('x_c', lower=0.2, upper=0.5)
prob.model.add_design_var('y_c', lower=0., upper=0.04)
prob.model.add_design_var('alpha_te', lower=-0.5, upper=0)
#prob.model.add_design_var('z_te')#, lower=0., upper=0.)
prob.model.add_design_var('b_8', lower=0.0000001, upper=0.06)
prob.model.add_design_var('b_15', lower=0.2, upper=1.)
prob.model.add_design_var('b_0', lower=0., upper=0.3)
prob.model.add_design_var('b_2', lower=-.1, upper=0.7)
prob.model.add_design_var('b_17', lower=0.7, upper=1.)
prob.model.add_objective('airfoil_cfd.c_d', scaler=1)
prob.model.add_constraint('airfoil_cfd.cabin_height',
lower=cabinHeigth * 0.99,
upper=cabinHeigth * 1.05)
prob.model.add_constraint('airfoil_cfd.c_l', lower=0.145, upper=.155)
prob.model.add_constraint('airfoil_cfd.c_m', lower=-0.05, upper=99.)
write_to_log(
'iterations,time,c_l,c_d,c_m,CL/CD,cfdIterations,cabin_height,offsetFront,angle,r_le,beta_te,x_t,y_t,gamma_le,x_c,y_c,alpha_te,z_te,b_8,b_15,b_0,b_17,b_2]))'
)
prob.setup()
prob.set_solver_print(level=0)
prob.model.approx_totals()
prob.run_driver()
print('done')
print('cabin frontOffset: ' + str(prob['airfoil_cfd.offsetFront']))
print('cabin angle: ' + str(-1. * prob['airfoil_cfd.angle']) + ' deg')
print('c_l= ' + str(prob['airfoil_cfd.c_l']))
print('c_d= ' + str(prob['airfoil_cfd.c_d']))
print('c_m= ' + str(prob['airfoil_cfd.c_m']))
print('execution counts airfoil cfd: ' +
str(prob.model.airfoil_cfd.executionCounter))
class AirfoilCFD(ExplicitComponent):
def setup(self):
######################
### needed Objects ###
self.bzFoil = BPAirfoil()
self.air = Airfoil(None)
#####################
### openMDAO init ###
### INPUTS
self.add_input('r_le', val=-0.05, desc='nose radius')
self.add_input('beta_te',
val=0.1,
desc='thickness angle trailing edge')
#self.add_input('dz_te', val=0., desc='thickness trailing edge')
self.add_input('x_t', val=0.3, desc='dickenruecklage')
#self.add_input('y_t', val=0.1, desc='max thickness')
self.add_input('gamma_le', val=0.5, desc='camber angle leading edge')
self.add_input('x_c', val=0.5, desc='woelbungsruecklage')
self.add_input('y_c', val=0.1, desc='max camber')
self.add_input('alpha_te', val=-0.1, desc='camber angle trailing edge')
#self.add_input('z_te', val=0., desc='camber trailing edge')
# bezier parameters
self.add_input('b_8', val=0.05, desc='')
self.add_input('b_15', val=0.75, desc='')
self.add_input('b_0', val=0.1, desc='')
self.add_input('b_2', val=0.25, desc='')
self.add_input('b_17', val=0.9, desc='')
# just for plotin
#self.add_input('offsetFront', val=0.1, desc='...')
#self.add_input('angle', val=.0, desc='...')
#self.add_input('cabin_height', val=.0, desc='...')
### OUTPUTS
self.add_output('c_d', val=.2)
self.add_output('c_l', val=.2)
self.add_output('c_m', val=.2)
self.add_output('y_t', val=0.1, desc='max thickness')
self.add_output('cabin_height', val=cabinHeigth)
self.add_output('angle', val=.0, desc='...')
self.add_output('offsetFront', val=0.1, desc='...')
self.declare_partials('*', '*', method='fd')
self.executionCounter = 0
self.prevAngle = -0.239
self.prevOffsetFront = 0.117
def calc_max_cabin_height(self, xFront, angle):
top, buttom = self.bzFoil.get_cooridnates_top_buttom(100)
if self.bzFoil.valid == False:
return False
xBack = xFront + cabinLength # inputs['length']
self.air.set_coordinates(top, buttom)
self.air.rotate(angle)
yMinButtom = max(self.air.get_buttom_y(xFront),
self.air.get_buttom_y(xBack))
yMaxTop = min(self.air.get_top_y(xFront), self.air.get_top_y(xBack))
height = yMaxTop - yMinButtom
return height
#outputs['cabin_height'] = height
def calc_min_y_t(self, offset_front, angle):
self.bzFoil.y_t = 0.07
init_height = self.calc_max_cabin_height(offset_front, angle)
if self.bzFoil.valid:
iterCounter = 0
height = init_height
while (abs(height - cabinHeigth) > 1e-6):
self.bzFoil.y_t += cabinHeigth - height
height = self.calc_max_cabin_height(offset_front, angle)
if height == False or self.bzFoil.y_t > 100 or self.bzFoil.y_t < 0.:
self.bzFoil.y_t = 9999.
return -1.
iterCounter += 1
#print('height: ' + str(height) + '\t' + str(self.bzFoil.y_t))
#print('calc_min_y_t: needed iterations= ' + str(iterCounter))
return height
#workaround for invalid airfoil
self.bzFoil.y_t = 9999.
return -1.
def optimize_cabin_angle(self, offset_front, angle):
iterCounter = 0
stepWidth = .01
iterStopStepWidth = 1e-3
height = self.calc_min_y_t(offset_front, angle)
act_min_y_t = self.bzFoil.y_t
while (abs(stepWidth) > iterStopStepWidth):
height = self.calc_min_y_t(offset_front, angle + stepWidth)
plus_min_y_t = self.bzFoil.y_t
if plus_min_y_t < act_min_y_t:
angle = angle + stepWidth
act_min_y_t = plus_min_y_t
else:
height = self.calc_min_y_t(offset_front, angle - stepWidth)
minus_min_y_t = self.bzFoil.y_t
if minus_min_y_t < act_min_y_t:
angle = angle - stepWidth
act_min_y_t = minus_min_y_t
else:
stepWidth = stepWidth / 10
iterCounter += 1
print('new angle: ' + str(angle) + '\t' + str(self.bzFoil.y_t))
print('optimize_cabin_angle: needed iterations= ' + str(iterCounter))
return angle
def optimize_cabin_front_offset(self, offset_front, angle):
iterCounter = 0
stepWidth = .01
iterStopStepWidth = 1e-3
newAngle = 0 #angle
act_angle = self.optimize_cabin_angle(offset_front, newAngle)
act_min_y_t = self.bzFoil.y_t
while (abs(stepWidth) > iterStopStepWidth):
plus_angle = self.optimize_cabin_angle(offset_front + stepWidth,
newAngle)
plus_min_y_t = self.bzFoil.y_t
if plus_min_y_t < act_min_y_t:
offset_front = offset_front + stepWidth
newAngle = plus_angle
act_min_y_t = plus_min_y_t
else:
minus_angle = self.optimize_cabin_angle(
offset_front - stepWidth, newAngle)
minus_min_y_t = self.bzFoil.y_t
if minus_min_y_t < act_min_y_t:
offset_front = offset_front - stepWidth
newAngle = minus_angle
act_min_y_t = minus_min_y_t
else:
stepWidth = stepWidth / 10
newAngle = act_angle
iterCounter += 1
print('new offset_front: ' + str(offset_front))
print('optimize_cabin_angle: needed iterations= ' + str(iterCounter))
return offset_front, newAngle
def compute(self, inputs, outputs):
error = False
self.bzFoil.r_le = inputs['r_le']
self.bzFoil.beta_te = inputs['beta_te']
#self.bzFoil.dz_te = inputs['dz_te']
self.bzFoil.x_t = inputs['x_t']
#self.bzFoil.y_t = inputs['y_t']
self.bzFoil.gamma_le = inputs['gamma_le']
self.bzFoil.x_c = inputs['x_c']
self.bzFoil.y_c = inputs['y_c']
self.bzFoil.alpha_te = inputs['alpha_te']
self.bzFoil.z_te = 0 #inputs['z_te']
self.bzFoil.b_8 = inputs['b_8']
self.bzFoil.b_15 = inputs['b_15']
self.bzFoil.b_0 = inputs['b_0']
self.bzFoil.b_2 = inputs['b_2']
self.bzFoil.b_17 = inputs['b_17']
projectName = PROJECT_NAME_PREFIX + '_%09d' % self.executionCounter
cfd = CFDrun(projectName)
airFoilCoords = self.bzFoil.generate_airfoil(
500,
show_plot=False,
save_plot_path=WORKING_DIR + '/' + projectName + '/airfoil.png',
param_dump_file=WORKING_DIR + '/' + projectName + '/airfoil.txt')
# check how high the cabin can be
outputs['offsetFront'], outputs[
'angle'] = self.optimize_cabin_front_offset(
self.prevOffsetFront, self.prevAngle)
self.prevAngle = outputs['angle']
outputs['cabin_height'] = self.calc_min_y_t(outputs['offsetFront'],
outputs['angle'])
#if self.bzFoil.valid:
outputs['y_t'] = self.bzFoil.y_t
print('new cabin_height= ' + str(outputs['cabin_height']))
if not self.bzFoil.valid:
#raise AnalysisError('AirfoilCFD: invalid BPAirfoil')
print('ERROR: AirfoilCFD, invalid BPAirfoil')
self.bzFoil.save_parameters_to_file(
WORKING_DIR + '/bz_error_' +
datetime.now().strftime('%Y-%m-%d_%H_%M_%S') + '.txt')
error = True
else:
self.bzFoil.plot_airfoil_with_cabin(outputs['offsetFront'],
cabinLength,
outputs['cabin_height'],
outputs['angle'],
show_plot=True,
save_plot_path=WORKING_DIR +
'/' + projectName +
'/airfoil_cabin.png')
### now we do cfd
top, buttom = self.bzFoil.get_cooridnates_top_buttom(500)
cfd.set_airfoul_coords(top, buttom)
cfd.c2d.pointsInNormalDir = 80
cfd.c2d.pointNrAirfoilSurface = 200
cfd.c2d.reynoldsNum = REYNOLD
cfd.construct2d_generate_mesh(scale=SCALE, plot=False)
cfd.su2_fix_mesh()
cfd.su2_solve(config)
#totalCL, totalCD, totalCM, totalE = cfd.su2_parse_results()
results = cfd.su2_parse_iteration_result()
cfd.clean_up()
if float(results['CD']) <= 0. or float(results['CD']) > 100.:
#raise AnalysisError('AirfoilCFD: c_d is out of range (cfd failed)')
print('ERROR: AirfoilCFD, c_d is out of range (cfd failed)')
error = True
outputs['c_d'] = results['CD']
outputs['c_l'] = results['CL']
outputs['c_m'] = results['CMz']
print('c_l= ' + str(outputs['c_l']))
print('c_d= ' + str(outputs['c_d']))
print('c_m= ' + str(outputs['c_m']))
print('c_l/c_d= ' + str(results['CL/CD']))
print('cfdIterations= ' + str(results['Iteration']))
write_to_log(
str(self.executionCounter) + ',' +
datetime.now().strftime('%H:%M:%S') + ',' +
str(outputs['c_l']) + ',' + str(outputs['c_d']) + ',' +
str(outputs['c_m']) + ',' + str(results['CL/CD']) + ',' +
str(results['Iteration']) + ',' +
str(outputs['cabin_height']) + ',' +
str(outputs['offsetFront']) + ',' + str(outputs['angle']) +
',' + str(inputs['r_le']) + ',' + str(inputs['beta_te']) +
',' + str(inputs['x_t']) + ',' + str(outputs['y_t']) + ',' +
str(inputs['gamma_le']) + ',' + str(inputs['x_c']) + ',' +
str(inputs['y_c']) + ',' + str(inputs['alpha_te']) + ',' +
str(self.bzFoil.z_te) + ',' + str(inputs['b_8']) + ',' +
str(inputs['b_15']) + ',' + str(inputs['b_0']) + ',' +
str(inputs['b_17']) + ',' + str(inputs['b_2']))
#workaround since raising an error seems to crash the optimization
if error:
outputs['c_d'] = 999.
outputs['c_l'] = 0.
outputs['c_m'] = 0.
self.executionCounter += 1
