})
h = 1e-40
# Setup aeroproblem, cfdsolver
ap = AeroProblem(name='mdo_tutorial',
alpha=1.8,
mach=0.80,
R=287.87,
altitude=10000.0,
areaRef=45.5,
chordRef=3.25,
evalFuncs=['cd', 'cmz', 'lift'])
ap.addDV('alpha')
ap.addDV('mach')
ap.addDV('altitude')
CFDSolver = ADFLOW(options=aeroOptions, debug=True)
if not 'complex' in sys.argv:
# Solve system
CFDSolver(ap, writeSolution=False)
funcs = {}
CFDSolver.evalFunctions(ap, funcs)
# Solve sensitivities
funcsSens = {}
CFDSolver.evalFunctionsSens(ap, funcsSens)
# Write values and derivatives out:
if MPI.COMM_WORLD.rank == 0:
for key in ['cd', 'cmz', 'lift']:
print 'funcs[%s]:' % key
reg_write(funcs['mdo_tutorial_%s' % key], 1e-10, 1e-10)
'nkswitchtol':1e-4,
'adjointl2convergence': 1e-16,
'nkls': 'non monotone',
'frozenturbulence':False,
'nkjacobianlag':2,
'blocksplitting': True
}
)
h = 1e-40
# Setup aeroproblem, cfdsolver
ap = AeroProblem(name='mdo_tutorial', alpha=1.8, mach=0.80, R=287.87,
altitude=10000.0, areaRef=45.5, chordRef=3.25, evalFuncs=['cl','cmz','drag'])
ap.addDV('alpha')
ap.addDV('mach')
CFDSolver = ADFLOW(options=aeroOptions)
if 'complex' in sys.argv:
DVGeo = DVGeometry('../inputFiles/mdo_tutorial_ffd.fmt', complex=True)
else:
DVGeo = DVGeometry('../inputFiles/mdo_tutorial_ffd.fmt', complex=False)
nTwist = 2
DVGeo.addRefAxis('wing', pyspline.Curve(x=numpy.linspace(5.0/4.0, 1.5/4.0+7.5, nTwist),
y=numpy.zeros(nTwist),
z=numpy.linspace(0,14, nTwist), k=2))
def twist(val, geo):
for i in xrange(nTwist):
geo.rot_z['wing'].coef[i] = val[i]
def span(val, geo):
# Span
ap = AeroProblem(name='fc_therm',
V=u_inf,
T=temp_air,
P=p_inf,
areaRef=1.0,
chordRef=1.0,
evalFuncs=['heatflux'],
alpha=0.0,
beta=0.00,
xRef=0.0,
yRef=0.0,
zRef=0.0)
# Create the solver
CFDSolver = ADFLOW(options=options, debug=False)
res = CFDSolver.getResidual(ap)
fluxes = CFDSolver.getHeatFluxes()
print(fluxes.imag / 1e-40)
# from python.pyADflow import ADFLOW
# CFDSolver = ADFLOW(options=options, debug=False)
# res = CFDSolver.getResidual(ap)
# # totalR0 = CFDSolver.getFreeStreamResidual(ap)
# # res /= totalR0
# # print('Norm of residual')
# # reducedSum = MPI.COMM_WORLD.reduce(numpy.sum(res**2))
# # print(reducedSum)
V=u_inf,
T=temp_air,
P=p_inf,
areaRef=1.0,
chordRef=1.0,
evalFuncs=['heatflux', 'cd', 'cl'],
alpha=0.0,
beta=0.00,
xRef=0.0,
yRef=0.0,
zRef=0.0)
ap.addDV('alpha', value=0.0, upper=10.0, lower=-10, scale=1e0)
# Create the solver
CFDSolver = ADFLOW(options=options, debug=False)
# CFDSolver.setMesh(USMesh(mesh_options))
# res = CFDSolver.getResidual(ap)
# totalR0 = CFDSolver.getFreeStreamResidual(ap)
# res /= totalR0
# print('Norm of residual')
# reducedSum = MPI.COMM_WORLD.reduce(numpy.sum(res**2))
# print(reducedSum)
# res = CFDSolver.getResidual(ap)
# CFDSolver.setAeroProblem(ap)
funcs = {}
CFDSolver(ap)
CFDSolver.evalFunctions(ap, funcs)
ap = AeroProblem(name='fc_therm',
V=u_inf,
T=temp_air,
P=p_inf,
areaRef=1.0,
chordRef=1.0,
evalFuncs=['heatflux'],
alpha=0.0,
beta=0.00,
xRef=0.0,
yRef=0.0,
zRef=0.0)
# Create the solver
CFDSolver = ADFLOW(options=options, debug=False)
#
res = CFDSolver.getResidual(ap)
# CFDSolver.callMasterRoutine(ap)
# CFDSolver(ap)
# # Create a common set of seeds
wDot = CFDSolver.getStatePerturbation(314)
xVDot = CFDSolver.getSpatialPerturbation(314)
dwBar = CFDSolver.getStatePerturbation(314)
fBar = CFDSolver.getSurfacePerturbation(314)
hfBar = CFDSolver.getSurfacePerturbation(314)[:, 1]
# # wBar = CFDSolver.computeJacobianVectorProductBwd(resBar=dwBar, wDeriv=True)
rho_inf = p_inf / (287 * temp_air)
ap = AeroProblem(name='fc_therm',
V=u_inf,
T=temp_air,
P=p_inf,
areaRef=1.0,
chordRef=1.0,
evalFuncs=['heatflux'],
alpha=0.0,
beta=0.00,
xRef=0.0,
yRef=0.0,
zRef=0.0)
# Create the solver
CFDSolver = ADFLOW(options=options, debug=False)
# res = CFDSolver.getResidual(ap)
# totalR0 = CFDSolver.getFreeStreamResidual(ap)
# res /= totalR0
# print('Norm of residual')
# reducedSum = MPI.COMM_WORLD.reduce(numpy.sum(res**2))
# print(reducedSum)
# res = CFDSolver.getResidual(ap)
# CFDSolver(ap, writesolution=False)
funcvalues, forces, fluxes = CFDSolver.callMasterRoutine(ap)
print('funcvalues', funcvalues)
print('forces', forces)
print('fluxes', fluxes)
def test6():
# ****************************************************************************
printHeader('MDO tutorial RANS Geometric Variables')
# ****************************************************************************
aeroOptions = copy.deepcopy(defOpts)
# Now set the options that need to be overwritten for this example:
aeroOptions.update(
{'gridfile': '../inputFiles/mdo_tutorial_rans.cgns',
'mgcycle':'2w',
'equationtype':'RANS',
'smoother':'dadi',
'nsubiterturb':3,
'nsubiter':3,
'cfl':1.5,
'cflcoarse':1.25,
'ncyclescoarse':250,
'ncycles':750,
'monitorvariables':['resrho','resturb','cl','cd','cmz','yplus','totalr'],
'usenksolver':True,
'l2convergence':1e-17,
'l2convergencecoarse':1e-2,
'nkswitchtol':1e-4,
'adjointl2convergence': 1e-16,
'nkls': 'non monotone',
'frozenturbulence':False,
'nkjacobianlag':2,
}
)
# Setup aeroproblem, cfdsolver
ap = AeroProblem(name='mdo_tutorial', alpha=1.8, mach=0.80,
altitude=10000.0, areaRef=45.5, chordRef=3.25, evalFuncs=['cl','cmz','drag'])
ap.addDV('alpha')
ap.addDV('mach')
CFDSolver = ADFLOW(options=aeroOptions)
if 'complex' in sys.argv:
DVGeo = DVGeometry('../inputFiles/mdo_tutorial_ffd.fmt', complex=True)
else:
DVGeo = DVGeometry('../inputFiles/mdo_tutorial_ffd.fmt', complex=False)
nTwist = 2
DVGeo.addRefAxis('wing', pyspline.Curve(x=numpy.linspace(5.0/4.0, 1.5/4.0+7.5, nTwist),
y=numpy.zeros(nTwist),
z=numpy.linspace(0,14, nTwist), k=2))
def twist(val, geo):
for i in xrange(nTwist):
geo.rot_z['wing'].coef[i] = val[i]
def span(val, geo):
# Span
C = geo.extractCoef('wing')
s = geo.extractS('wing')
for i in xrange(len(C)-1):
C[-1, 2] = C[-1, 2] + val[0]
geo.restoreCoef(C, 'wing')
DVGeo.addGeoDVGlobal('twist', [0]*nTwist, twist, lower=-10, upper=10, scale=1.0)
DVGeo.addGeoDVGlobal('span', [0], span, lower=-10, upper=10, scale=1.0)
DVGeo.addGeoDVLocal('shape', lower=-0.5, upper=0.5, axis='y', scale=10.0)
mesh = MBMesh(options={'gridFile':'../inputFiles/mdo_tutorial_rans.cgns'})
CFDSolver.setMesh(mesh)
CFDSolver.setDVGeo(DVGeo)
#Aeroproblem must be set before we can call DVGeo.setDesignVars
CFDSolver.setAeroProblem(ap)
if not 'complex' in sys.argv:
# Solve system
CFDSolver(ap, writeSolution=False)
funcs = {}
CFDSolver.evalFunctions(ap, funcs)
# Solve sensitivities
funcsSens = {}
CFDSolver.evalFunctionsSens(ap, funcsSens)
# Write values and derivatives out:
if MPI.COMM_WORLD.rank == 0:
for key in ['cl','cmz','drag']:
print 'funcs[%s]:'%key
reg_write(funcs['mdo_tutorial_%s'%key],1e-10,1e-10)
# Now write the derivatives in the same order the CS will do them:
print ('Twist[0] Derivatives:')
reg_write(funcsSens['mdo_tutorial_cl']['twist'][0][0], 1e-10,1e-10)
reg_write(funcsSens['mdo_tutorial_cmz']['twist'][0][0], 1e-10,1e-10)
reg_write(funcsSens['mdo_tutorial_drag']['twist'][0][0], 1e-10,1e-10)
print ('Span Derivatives:')
reg_write(funcsSens['mdo_tutorial_cl']['span'][0], 1e-10,1e-10)
reg_write(funcsSens['mdo_tutorial_cmz']['span'][0], 1e-10,1e-10)
reg_write(funcsSens['mdo_tutorial_drag']['span'][0], 1e-10,1e-10)
print ('shape[13] Derivatives:')
reg_write(funcsSens['mdo_tutorial_cl']['shape'][0][13], 1e-10,1e-10)
reg_write(funcsSens['mdo_tutorial_cmz']['shape'][0][13], 1e-10,1e-10)
reg_write(funcsSens['mdo_tutorial_drag']['shape'][0][13], 1e-10,1e-10)
print ('mach Derivatives:')
reg_write(funcsSens['mdo_tutorial_cl']['mach_mdo_tutorial'], 1e-10,1e-10)
reg_write(funcsSens['mdo_tutorial_cmz']['mach_mdo_tutorial'], 1e-10,1e-10)
reg_write(funcsSens['mdo_tutorial_drag']['mach_mdo_tutorial'], 1e-10,1e-10)
else:
# For the complex....we just do successive perturbation
for ii in range(4):
xRef = {'twist':[0.0, 0.0], 'span':[0.0], 'shape':numpy.zeros(72, dtype='D'), 'mach_mdo_tutorial':0.8}
if ii == 0:
xRef['twist'][0] += h*1j
elif ii == 1:
xRef['span'][0] += h*1j
elif ii == 2:
xRef['shape'][13] += h*1j
else:
xRef['mach_mdo_tutorial']+=h*1j
ap.setDesignVars(xRef)
CFDSolver.resetFlow(ap)
DVGeo.setDesignVars(xRef)
CFDSolver(ap, writeSolution=False)
funcs = {}
CFDSolver.evalFunctions(ap, funcs)
if MPI.COMM_WORLD.rank == 0:
if ii == 0:
for key in ['cl','cmz','drag']:
print 'funcs[%s]:'%key
reg_write(numpy.real(funcs['mdo_tutorial_%s'%key]),1e-10,1e-10)
if ii == 0:
print ('Twist[0] Derivatives:')
elif ii == 1:
print ('Span Derivatives:')
elif ii == 2:
print ('shape[13] Derivatives:')
elif ii == 3:
print ('mach Derivatives:')
for key in ['cl','cmz','drag']:
deriv = numpy.imag(funcs['mdo_tutorial_%s'%key])/h
reg_write(deriv,1e-10,1e-10)
del CFDSolver
del mesh
def test5():
# ****************************************************************************
printHeader('MDO tutorial RANS Aerodynamic Variables')
# ****************************************************************************
aeroOptions = copy.deepcopy(defOpts)
# Now set the options that need to be overwritten for this example:
aeroOptions.update(
{'gridfile': '../inputFiles/mdo_tutorial_rans.cgns',
'mgcycle':'2w',
'equationtype':'RANS',
'smoother':'dadi',
'nsubiterturb':3,
'nsubiter':3,
'cfl':1.5,
'cflcoarse':1.25,
'ncyclescoarse':250,
'ncycles':750,
'monitorvariables':['resrho','resturb','cl','cd','cmz','yplus','totalr'],
'usenksolver':True,
'l2convergence':1e-17,
'l2convergencecoarse':1e-2,
'nkswitchtol':1e-4,
'adjointl2convergence': 1e-16,
'nkls': 'non monotone',
'frozenturbulence':False,
'nkjacobianlag':2,
}
)
# Setup aeroproblem, cfdsolver
ap = AeroProblem(name='mdo_tutorial', alpha=1.8, mach=0.80,
altitude=10000.0, areaRef=45.5, chordRef=3.25, evalFuncs=['cd','cmz','lift'])
ap.addDV('alpha')
ap.addDV('mach')
ap.addDV('altitude')
CFDSolver = ADFLOW(options=aeroOptions,debug=True)
if not 'complex' in sys.argv:
# Solve system
CFDSolver(ap, writeSolution=False)
funcs = {}
CFDSolver.evalFunctions(ap, funcs)
# Solve sensitivities
funcsSens = {}
CFDSolver.evalFunctionsSens(ap, funcsSens)
# Write values and derivatives out:
if MPI.COMM_WORLD.rank == 0:
for key in ['cd','cmz','lift']:
print 'funcs[%s]:'%key
reg_write(funcs['mdo_tutorial_%s'%key],1e-10,1e-10)
# Now write the derivatives in the same order the CS will do them:
print ('Alpha Derivatives:')
reg_write(funcsSens['mdo_tutorial_cd']['alpha_mdo_tutorial'], 1e-10,1e-10)
reg_write(funcsSens['mdo_tutorial_cmz']['alpha_mdo_tutorial'], 1e-10,1e-10)
reg_write(funcsSens['mdo_tutorial_lift']['alpha_mdo_tutorial'], 1e-10,1e-10)
print ('Mach Derivatives:')
reg_write(funcsSens['mdo_tutorial_cd']['mach_mdo_tutorial'], 1e-10,1e-10)
reg_write(funcsSens['mdo_tutorial_cmz']['mach_mdo_tutorial'], 1e-10,1e-10)
reg_write(funcsSens['mdo_tutorial_lift']['mach_mdo_tutorial'], 1e-10,1e-10)
print ('Altitude Derivatives:')
reg_write(funcsSens['mdo_tutorial_cd']['altitude_mdo_tutorial'], 1e-8,1e-8)
reg_write(funcsSens['mdo_tutorial_cmz']['altitude_mdo_tutorial'], 1e-8,1e-8)
reg_write(funcsSens['mdo_tutorial_lift']['altitude_mdo_tutorial'], 1e-8,1e-8)
else:
# For the complex....we just do successive perturbation
for ii in range(3):
ap.alpha = 1.8
ap.mach = 0.80
ap.altitude = 10000.0
if ii == 0:
ap.alpha += h*1j
elif ii == 1:
ap.mach += h*1j
else:
ap.altitude += h*1j
CFDSolver.resetFlow(ap)
CFDSolver(ap, writeSolution=False)
funcs = {}
CFDSolver.evalFunctions(ap, funcs)
if MPI.COMM_WORLD.rank == 0:
if ii == 0:
for key in ['cd','cmz','lift']:
print 'funcs[%s]:'%key
reg_write(numpy.real(funcs['mdo_tutorial_%s'%key]),1e-10,1e-10)
if ii == 0:
print ('Alpha Derivatives:')
for key in ['cd','cmz','lift']:
deriv = numpy.imag(funcs['mdo_tutorial_%s'%key])/h
reg_write(deriv,1e-10,1e-10)
elif ii == 1:
print ('Mach Derivatives:')
for key in ['cd','cmz','lift']:
deriv = numpy.imag(funcs['mdo_tutorial_%s'%key])/h
reg_write(deriv,1e-10,1e-10)
else:
print ('AltitudeDerivatives:')
for key in ['cd','cmz','lift']:
deriv = numpy.imag(funcs['mdo_tutorial_%s'%key])/h
reg_write(deriv,1e-10,1e-10)
del CFDSolver