'NKSubSpaceSize':400,
'NKASMOverlap':4,
'NKPCILUFill':4,
'NKJacobianLag':5,
'nkswitchtol':1e-6,
'nkouterpreconits':3,
'NKInnerPreConIts':3,
'writeSurfaceSolution':False,
'writeVolumeSolution':False,
'frozenTurbulence':False,
'restartADjoint':False,
}
# Create solver
CFDSolver = ADFLOW(options=aeroOptions, comm=comm)
CFDSolver.addLiftDistribution(200, 'z')
#rst adflow (end)
# ======================================================================
# Set up flow conditions with AeroProblem
# ======================================================================
#rst aeroproblem (beg)
ap = AeroProblem(name='fc', alpha=alpha, mach=mach, altitude=alt,
areaRef=1.0, chordRef=1.0, evalFuncs=['cl','cd'])
# Add angle of attack variable
ap.addDV('alpha', value=alpha, lower=0, upper=10.0, scale=1.0)
#rst aeroproblem (end)
# ======================================================================
# Geometric Design Variable Set-up
# ======================================================================
#rst dvgeo (beg)
# Create DVGeometry object
# ANK Solver Parameters
"useANKSolver": True,
# NK Solver Parameters
"useNKSolver": True,
"nkswitchtol": 1e-6,
# Termination Criteria
"L2Convergence": 1e-10,
"L2ConvergenceCoarse": 1e-2,
"nCycles": 10000,
# Adjoint Parameters
"adjointL2Convergence": 1e-10,
}
# Create solver
CFDSolver = ADFLOW(options=aeroOptions, comm=comm)
CFDSolver.addLiftDistribution(150, "z")
CFDSolver.addSlices("z", np.linspace(0.1, 14, 10))
# rst adflow (end)
# ======================================================================
# Set up flow conditions with AeroProblem
# ======================================================================
# rst aeroproblem (beg)
ap = AeroProblem(name="wing",
alpha=1.5,
mach=0.8,
altitude=10000,
areaRef=45.5,
chordRef=3.25,
evalFuncs=["cl", "cd"])
# Add angle of attack variable
# Zipper mesh option
'debugzipper':False,
'usezippermesh':True,
'nrefine':10, # number of times to run IHC cycle
'nearwalldist':0.1,
'oversetpriority':oversetpriority
}
# Create solver
CFDSolver = ADFLOW(options=aeroOptions)
#rst end_options
# Save the lift distribution for the front wing
CFDSolver.addLiftDistribution(200, 'z', groupName='wing_front')
# Save the lift distribution for the back wing
CFDSolver.addLiftDistribution(200, 'z', groupName='wing_back')
# Save the total lift distribution
CFDSolver.addLiftDistribution(200, 'z')
#rst end_dist
ap = AeroProblem(name='fc', mach=0.3, altitude=1000, areaRef=0.64*0.24*2, alpha=3., chordRef=0.24, evalFuncs = ['cl', 'cd'])
CFDSolver(ap)
funcs = {}
CFDSolver.evalFunctions(ap, funcs)
# Print the evaluated functions
if MPI.COMM_WORLD.rank == 0:
print(funcs)
