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']))
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):
def setup(self):
#####################
### 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='...')
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
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.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.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
height = self.fit_cabin(inputs['offsetFront'], inputs['angle'])
if self.bzFoil.valid:
iterCounter = 0
while (abs(height - cabinHeigth) > 1e-6):
self.bzFoil.y_t += cabinHeigth - height
height = self.fit_cabin(inputs['offsetFront'], inputs['angle'])
if height == False:
break
iterCounter += 1
outputs['cabin_height'] = height
outputs['y_t'] = self.bzFoil.y_t
print('new cabin_height= ' + str(outputs['cabin_height']))
print('needed iterations= ' + str(iterCounter))
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,
outputs['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)
#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(inputs['offsetFront']) + ',' + str(inputs['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
def plot_airfoil_with_cabin(self,
offsetFront,
length,
height,
angle,
show_plot=True,
save_plot_path='',
clear_plot=True,
ax=None):
top, buttom = self.get_cooridnates_top_buttom(500)
#if bzFoil.valid == False:
# return False, False
air = Airfoil(None)
air.set_coordinates(top, buttom)
air.rotate(angle)
# air.rotate(angle)
px_ul = offsetFront
px_ur = offsetFront + length
py_ul = max(air.get_buttom_y(px_ul), air.get_buttom_y(px_ur))
py_ur = py_ul
px_ol = px_ul
px_or = px_ur
py_ol = min(air.get_top_y(px_ol), air.get_top_y(px_or))
py_or = py_ol
print('geometrical calculated height = ' + str(py_ol - py_ul))
(px_ol, py_ol) = air.rotatePoint((0, 0), (px_ol, py_ol), -angle)
(px_ul, py_ul) = air.rotatePoint((0, 0), (px_ul, py_ul), -angle)
# py_ur = air.get_buttom_y(px_ur)
# px_or = px_ur
# py_or = py_ur + height
(px_or, py_or) = air.rotatePoint((0, 0), (px_or, py_or), -angle)
(px_ur, py_ur) = air.rotatePoint((0, 0), (px_ur, py_ur), -angle)
air.rotate(0.)
#fig, ax = air.plotAirfoil(showPlot=False, showPoints=False, ax=ax)
ax.plot([px_ol, px_ul, px_ur, px_or, px_ol],
[py_ol, py_ul, py_ur, py_or, py_ol],
'rx-',
label='cabin',
color='#AD031B')
#plt.show()
plt.axis('equal')
if save_plot_path != '':
fig.set_size_inches(18.5, 10.5)
#plt.savefig(save_plot_path, dpi=900)
plt.savefig(save_plot_path + '.svg', dpi=900)
if show_plot:
plt.show()
if clear_plot:
plt.clf()
'''
#angle = 0.
#offsetFront = 0.11
#length = 0.55
air = Airfoil(None)
air.set_coordinates(self.topCoords, self.buttomCoords)
air.rotate(angle)
px_ul = offsetFront
px_ur = offsetFront + length
py_ul = max(air.get_buttom_y(px_ul), air.get_buttom_y(px_ur))
py_ur = py_ul
px_ol = px_ul
px_or = px_ur
py_ol = min(air.get_top_y(px_ol), air.get_top_y(px_or))
py_or = py_ol
print('geometrical calculated height = ' + str(py_ol - py_ul))
(px_ol, py_ol) = air.rotatePoint((0, 0), (px_ol, py_ol), -angle)
(px_ul, py_ul) = air.rotatePoint((0, 0), (px_ul, py_ul), -angle)
# py_ur = air.get_buttom_y(px_ur)
# px_or = px_ur
# py_or = py_ur + height
(px_or, py_or) = air.rotatePoint((0, 0), (px_or, py_or), -angle)
(px_ur, py_ur) = air.rotatePoint((0, 0), (px_ur, py_ur), -angle)
air.rotate(0.)
fig, ax = air.plotAirfoil(showPlot=False, showPoints=False)
ax.plot([px_ol, px_ul, px_ur, px_or, px_ol], [py_ol, py_ul, py_ur, py_or, py_ol], 'rx-')
'''
"""
class CFDrun:
def __init__(self, project_name, used_cores=SU2_USED_CORES):
# create project dir if necessary
self.projectDir = WORKING_DIR + '/' + project_name
# create project dir if necessary
if not os.path.isdir(self.projectDir):
os.mkdir(self.projectDir)
self.su2 = SU2(SU2_BIN_PATH,
used_cores=used_cores,
mpi_exec=OS_MPI_COMMAND)
self.foilCoord = None
self.gmsh = Gmsh(GMSH_EXE_PATH)
self.c2d = Construct2d(CONSTRUCT2D_EXE_PATH)
def load_airfoil_from_file(self, file_name):
self.airfoil = Airfoil(file_name)
self.foilCoord = self.airfoil.get_sorted_point_list()
#def load_airfoil_bp(self):
# bp = BPAirfoil()
# self.foilCoord = bp.generate_airfoil(500, show_plot=False)
def set_airfoul_coords(self, buttom, top):
#self.foilCoord = coords
self.airfoil = Airfoil(None)
self.airfoil.set_coordinates(top, buttom)
self.foilCoord = self.airfoil.get_sorted_point_list()
def gmsh_generate_mesh(self, scale=1.):
print('start meshing with gmsh...')
self.gmsh.generate_geo_file(self.foilCoord,
'airfoilMesh.geo',
1000,
working_dir=self.projectDir,
scale=scale)
self.gmsh.run_2d_geo_file('airfoilMesh.geo',
'airfoilMesh.su2',
working_dir=self.projectDir)
def construct2d_generate_mesh(self,
scale=1.,
plot=False,
wake_extension=0):
print('start meshing with construct2d...')
self.airfoil.write_to_dat('airfoil.dat', working_dir=self.projectDir)
self.c2d.run_mesh_generatoin('airfoil.dat',
working_dir=self.projectDir)
#p2_to_su2_ogrid(self.projectDir + '/' + 'airfoil.p3d')
c2dParser = Construct2dParser(self.projectDir + '/' + 'airfoil.p3d')
if wake_extension > 0:
c2dParser.extend_wake(wake_extension)
c2dParser.p3d_to_su2_cgrid(self.projectDir + '/' + 'airfoilMesh.su2',
scale=scale)
if plot:
print('saving mesh plot...')
c2dParser.plot_mesh(scale=scale)
#if os.path.isfile(self.projectDir + '/' + 'airfoilMesh.su2'):
# os.remove(self.projectDir + '/' + 'airfoilMesh.su2')
#os.rename(self.projectDir + '/' + 'airfoil.su2', self.projectDir + '/' + 'airfoilMesh.su2')
def su2_fix_mesh(self):
print('start mesh-fixing...')
self.su2.fix_mesh('airfoilMesh.su2',
'airfoilMeshFixed.su2',
working_dir=self.projectDir)
def su2_solve(self, config):
print('start solving...')
self.su2.write_single_core_batch_file(working_dir=self.projectDir)
return self.su2.run_cfd('airfoilMeshFixed.su2',
config,
working_dir=self.projectDir)
def su2_parse_results(self):
print('parse results...')
totalCL, totalCD, totalCM, totalE = self.su2.parse_force_breakdown(
'forces_breakdown.dat', working_dir=self.projectDir)
return totalCL, totalCD, totalCM, totalE
def su2_parse_iteration_result(self):
print('parsing cfd iteration results')
return self.su2.parse_result_from_history('history.vtk',
working_dir=self.projectDir)
def clean_up(self):
print('clean up...')
if os.path.isfile(self.projectDir + '/airfoilMesh.su2'):
os.remove(self.projectDir + '/airfoilMesh.su2')
if os.path.isfile(self.projectDir + '/airfoil_stats.p3d'):
os.remove(self.projectDir + '/airfoil_stats.p3d')
if os.path.isfile(self.projectDir + '/airfoil.p3d'):
os.remove(self.projectDir + '/airfoil.p3d')
if os.path.isfile(self.projectDir + '/airfoil.nmf'):
os.remove(self.projectDir + '/airfoil.nmf')
#if os.path.isfile(self.projectDir + '/restart_flow.dat'):
# os.remove(self.projectDir + '/restart_flow.dat')
if os.path.isfile(self.projectDir + '/original_grid.dat'):
os.remove(self.projectDir + '/original_grid.dat')
if os.path.isfile(self.projectDir + '/meshFix.cfg'):
os.remove(self.projectDir + '/meshFix.cfg')
if os.path.isfile(self.projectDir + '/surface_analysis.vtk'):
os.remove(self.projectDir + '/surface_analysis.vtk')