def regression_test(self, handler, solve=False):
'''
This is where the actual testing happens.
'''
import copy
from baseclasses import AeroProblem
from commonUtils import standard_test, adflowDefOpts, defaultFuncList
gridFile = 'input_files/mdo_tutorial_euler_scalar_jst.cgns'
options = copy.copy(adflowDefOpts)
options.update({
'gridfile':
gridFile,
'mgcycle':
'2w',
'ncyclescoarse':
250,
'ncycles':
500,
'monitorvariables': ['cpu', 'resrho', 'cl', 'cd', 'cmz', 'totalr'],
'usenksolver':
True,
'l2convergence':
1e-14,
'l2convergencecoarse':
1e-2,
'nkswitchtol':
1e-2,
'adjointl2convergence':
1e-14,
'solutionprecision':
'double',
'gridprecision':
'double',
})
# Setup aeroproblem, cfdsolver, mesh and geometry.
ap = AeroProblem(name='mdo_tutorial',
alpha=1.8,
mach=0.80,
P=20000.0,
T=220.0,
areaRef=45.5,
chordRef=3.25,
beta=0.0,
R=287.87,
xRef=0.0,
yRef=0.0,
zRef=0.0,
evalFuncs=defaultFuncList)
if not solve:
options['restartfile'] = gridFile
# Create the solver
CFDSolver = ADFLOW(options=options, debug=True)
standard_test(handler, CFDSolver, ap, solve)
def setup_cb(comm):
# Create the solver
CFDSolver = ADFLOW(options=options, comm=comm, debug=False)
# Setup geometry/mesh
DVGeo = DVGeometry(ffdFile)
nTwist = 6
DVGeo.addRefAxis(
'wing',
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 range(nTwist):
geo.rot_z['wing'].coef[i] = val[i]
DVGeo.addGeoDVGlobal('twist', [0] * nTwist,
twist,
lower=-10,
upper=10,
scale=1.0)
DVGeo.addGeoDVLocal('shape', lower=-0.5, upper=0.5, axis='y', scale=10.0)
mesh = USMesh(options=meshOptions, comm=comm)
CFDSolver.setMesh(mesh)
CFDSolver.setDVGeo(DVGeo)
return CFDSolver, mesh, DVGeo, None
def setup_cb(comm):
solver = ADFLOW(options=options, comm=comm, debug=True)
solver.addIntegrationSurface('../inputFiles/integration_plane_viscous.fmt',
'viscous_plane')
solver.finalizeUserIntegrationSurfaces()
solver.addFamilyGroup('upstream', ['inlet'])
solver.addFamilyGroup('downstream', ['outlet'])
solver.addFamilyGroup('all_flow', ['inlet', 'outlet'])
solver.addFamilyGroup('output_fam', ['all_flow', 'allWalls'])
solver.addFunction('mdot', 'upstream', name="mdot_up")
solver.addFunction('mdot', 'downstream', name="mdot_down")
solver.addFunction('mdot', 'viscous_plane', name="mdot_plane")
solver.addFunction('mavgptot', 'downstream', name="mavgptot_down")
solver.addFunction('mavgptot', 'upstream', name="mavgptot_up")
solver.addFunction('mavgptot', 'viscous_plane', name="mavgptot_plane")
solver.addFunction('aavgptot', 'downstream', name="aavgptot_down")
solver.addFunction('aavgptot', 'upstream', name="aavgptot_up")
solver.addFunction('aavgptot', 'viscous_plane', name="aavgptot_plane")
solver.addFunction('mavgttot', 'downstream', name="mavgttot_down")
solver.addFunction('mavgttot', 'upstream', name="mavgttot_up")
solver.addFunction('mavgttot', 'viscous_plane', name="mavgttot_plane")
solver.addFunction('mavgps', 'downstream', name="mavgps_down")
solver.addFunction('mavgps', 'upstream', name="mavgps_up")
solver.addFunction('mavgps', 'viscous_plane', name="mavgps_plane")
solver.addFunction('aavgps', 'downstream', name="aavgps_down")
solver.addFunction('aavgps', 'upstream', name="aavgps_up")
solver.addFunction('aavgps', 'viscous_plane', name="aavgps_plane")
solver.setOption('ncycles', 1000)
return solver, None, None, None
temp_air = 273 # kelvin
Pr = 0.72
mu = 1.81e-5 # kg/(m * s)
# 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)
def setup_cb(comm):
# Create the solver
CFDSolver = ADFLOW(options=options, debug=False)
return CFDSolver, None, None, None
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)
def setup_cb(comm):
CFDSolver = ADFLOW(options=options, comm=comm)
CFDSolver.addSlices('z', [0.5])
CFDSolver(ap)
return CFDSolver, None, None, None
def setup_cb(comm):
solver = ADFLOW(options=options, comm=comm, debug=False)
solver.addFamilyGroup('upstream', ['INFLOW'])
solver.addFamilyGroup('downstream', ['OUTFLOW'])
solver.addFamilyGroup('all_flow', ['INFLOW', 'OUTFLOW'])
solver.addFunction('mdot', 'upstream', name="mdot_up")
solver.addFunction('mdot', 'downstream', name="mdot_down")
solver.addFunction('mavgptot', 'downstream', name="mavgptot_down")
solver.addFunction('mavgptot', 'upstream', name="mavgptot_up")
solver.addFunction('aavgptot', 'downstream', name="aavgptot_down")
solver.addFunction('aavgptot', 'upstream', name="aavgptot_up")
solver.addFunction('mavgttot', 'downstream', name="mavgttot_down")
solver.addFunction('mavgttot', 'upstream', name="mavgttot_up")
solver.addFunction('mavgps', 'downstream', name="mavgps_down")
solver.addFunction('mavgps', 'upstream', name="mavgps_up")
solver.addFunction('aavgps', 'downstream', name="aavgps_down")
solver.addFunction('aavgps', 'upstream', name="aavgps_up")
solver.addFunction('mavgmn', 'downstream', name="mavgmn_down")
solver.addFunction('mavgmn', 'upstream', name="mavgmn_up")
solver.addFunction(
'drag', 'all_flow',
name="thrust") # this naming makes it seem like wishful thinking
solver.addFunction('dragpressure', 'all_flow', name="thrust_pressure")
solver.addFunction('dragviscous', 'all_flow', name="thrust_viscous")
solver.addFunction('dragmomentum', 'all_flow', name="thrust_momentum")
return solver, None, None, None