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
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
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