# Rex =
u_inf = 30 # m/s\
p_inf = 101e3
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)
# 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].reshape((len(fBar), 1))
# wBar = CFDSolver.computeJacobianVectorProductBwd(resBar=dwBar, wDeriv=True)
# CFDSolver.computeDotProductTest(fBar=True, xVDot=True)
# CFDSolver.computeDotProductTest(hfBar=True, xVDot=True)
# CFDSolver.computeDotProductTest(hfBar=True, wDot=True)
def regression_test(self, handler, solve=False):
'''
This is where the actual testing happens.
'''
gridFile = 'input_files/conic_conv_nozzle_mb.cgns'
integrationSurf = 'input_files/integration_plane_viscous.fmt'
options = copy.copy(adflowDefOpts)
options.update({
'gridfile':
gridFile,
'equationType':
'euler',
'smoother':
'dadi',
'nsubiter':
3,
'CFL':
4.0,
'CFLCoarse':
1.25,
'MGCycle':
'sg',
'MGStartLevel':
-1,
'nCyclesCoarse':
250,
'nCycles':
1000,
'nkcfl0':
1e10,
'monitorvariables': ['cpu', 'resrho', 'cl', 'cd'],
'volumevariables': ['blank'],
'surfacevariables': ['mach', 'cp', 'vx', 'vy', 'vz', 'blank'],
'useNKSolver':
True,
'nkswitchtol':
.01,
'nkadpc':
True,
'nkjacobianlag':
5,
'nkouterpreconits':
3,
'nkinnerpreconits':
2,
'L2Convergence':
1e-10,
'L2ConvergenceCoarse':
1e-4,
'adjointl2convergence':
1e-6,
'forcesAsTractions':
True,
'debugzipper':
True,
'nearwalldist':
.001,
'nkls':
'none',
'solutionprecision':
'double',
'adjointsubspacesize':
200,
'outerpreconits':
3,
'zipperSurfaceFamily':
'output_fam',
'flowtype':
'internal',
})
if not solve:
options['restartfile'] = gridFile
# Setup aeroproblem
ap = AeroProblem(name='nozzle',
alpha=90.0,
mach=0.5,
altitude=0,
areaRef=1.0,
chordRef=1.0,
R=287.87,
evalFuncs=[
'mdot_up',
'mdot_down',
'mdot_plane',
'mavgptot_up',
'mavgptot_down',
'mavgptot_plane',
'aavgptot_up',
'aavgptot_down',
'aavgptot_plane',
'mavgttot_up',
'mavgttot_down',
'mavgttot_plane',
'mavgps_up',
'mavgps_down',
'mavgps_plane',
'aavgps_up',
'aavgps_down',
'aavgps_plane',
])
# ap.setBCVar('Pressure', 79326.7, 'downstream')
# ap.addDV('Pressure', family='downstream')
# ap.setBCVar('PressureStagnation', 100000.0, 'upstream')
# ap.addDV('PressureStagnation', family='upstream')
# ap.setBCVar('TemperatureStagnation', 500.0, 'upstream')
# ap.addDV('TemperatureStagnation', family='upstream')
# Create the solver
CFDSolver = ADFLOW(options=options)
# CFDSolver.addIntegrationSurface(integrationSurf, 'viscous_plane')
# CFDSolver.finalizeUserIntegrationSurfaces()
CFDSolver.addFamilyGroup('upstream', ['inlet'])
CFDSolver.addFamilyGroup('downstream', ['outlet'])
CFDSolver.addFamilyGroup('all_flow', ['inlet', 'outlet'])
CFDSolver.addFamilyGroup('output_fam', ['all_flow', 'allWalls'])
CFDSolver.addFunction('mdot', 'upstream', name="mdot_up")
CFDSolver.addFunction('mdot', 'downstream', name="mdot_down")
# CFDSolver.addFunction('mdot', 'viscous_plane', name="mdot_plane")
CFDSolver.addFunction('mavgptot', 'downstream', name="mavgptot_down")
CFDSolver.addFunction('mavgptot', 'upstream', name="mavgptot_up")
# CFDSolver.addFunction('mavgptot', 'viscous_plane', name="mavgptot_plane")
CFDSolver.addFunction('aavgptot', 'downstream', name="aavgptot_down")
CFDSolver.addFunction('aavgptot', 'upstream', name="aavgptot_up")
# CFDSolver.addFunction('aavgptot', 'viscous_plane', name="aavgptot_plane")
CFDSolver.addFunction('mavgttot', 'downstream', name="mavgttot_down")
CFDSolver.addFunction('mavgttot', 'upstream', name="mavgttot_up")
# CFDSolver.addFunction('mavgttot', 'viscous_plane', name="mavgttot_plane")
CFDSolver.addFunction('mavgps', 'downstream', name="mavgps_down")
CFDSolver.addFunction('mavgps', 'upstream', name="mavgps_up")
# CFDSolver.addFunction('mavgps', 'viscous_plane', name="mavgps_plane")
CFDSolver.addFunction('aavgps', 'downstream', name="aavgps_down")
CFDSolver.addFunction('aavgps', 'upstream', name="aavgps_up")
# CFDSolver.addFunction('aavgps', 'viscous_plane', name="aavgps_plane")
CFDSolver.setOption('ncycles', 1000)
# Run test
# CFDSolver(ap)
# Check the residual
# CFDSolver.setAeroProblem(ap)
res = CFDSolver.getResidual(ap)
# totalR0, totalRStart, totalRFinal = CFDSolver.getResNorms()
# res /= totalR0
handler.par_add_norm(res, 1e-10, 1e-10)
# Get and check the states
handler.par_add_norm(CFDSolver.getStates(), 1e-10, 1e-10)
funcs = {}
CFDSolver.evalFunctions(ap, funcs)
handler.root_add_dict(funcs, 1e-10, 1e-10)