"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
ap.addDV("alpha", value=1.5, lower=0, upper=10.0, scale=0.1)
# 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
FFDFile = 'ffd.xyz'
DVGeo = DVGeometry(FFDFile)
DVGeo.addGeoDVLocal('shape', lower=-0.05, upper=0.05, axis='y', scale=1.0)
span = 1.0
pos = numpy.array([0.5])*span
CFDSolver.addSlices('z',pos,sliceType='absolute')
# Add DVGeo object to CFD solver
CFDSolver.setDVGeo(DVGeo)
#rst dvgeo (end)
# ======================================================================
# DVConstraint Setup
# ======================================================================
#rst dvcon (beg)
DVCon = DVConstraints()
DVCon.setDVGeo(DVGeo)
# Only ADflow has the getTriangulatedSurface Function
DVCon.setSurface(CFDSolver.getTriangulatedMeshSurface())
ap.addDV("alpha", value=alpha[i], lower=0, upper=10.0, scale=1.0)
aeroProblems.append(ap)
# rst aeroproblem (end)
# ======================================================================
# Geometric Design Variable Set-up
# ======================================================================
# rst dvgeo (beg)
# Create DVGeometry object
FFDFile = "ffd.xyz"
DVGeo = DVGeometry(FFDFile) # DVGeo = DVGeometry_FFD(FFDFile)
DVGeo.addGeoDVLocal("shape", lower=-0.05, upper=0.05, axis="y", scale=1.0)
span = 1.0
pos = np.array([0.5]) * span
CFDSolver.addSlices("z", pos, sliceType="absolute")
# Add DVGeo object to CFD solver
CFDSolver.setDVGeo(DVGeo)
# rst dvgeo (end)
# ======================================================================
# DVConstraint Setup
# ======================================================================
# rst dvcon (beg)
DVCon = DVConstraints() # DVCon = DVConstraints_FFD_data()
DVCon.setDVGeo(DVGeo)
# Only ADflow has the getTriangulatedSurface Function
DVCon.setSurface(CFDSolver.getTriangulatedMeshSurface())
# Le/Te constraints
# NK Solver Parameters
'useNKSolver': True,
'nkswitchtol': 1e-4,
# Termination Criteria
'L2Convergence': 1e-6,
'L2ConvergenceCoarse': 1e-2,
'nCycles': 1000,
}
#rst Start ADflow
# Create solver
CFDSolver = ADFLOW(options=aeroOptions)
# Add features
CFDSolver.addLiftDistribution(150, 'z')
CFDSolver.addSlices('z', numpy.linspace(0.1, 14, 10))
#rst Create AeroProblem
ap = AeroProblem(name='wing',
mach=0.8,
altitude=10000,
alpha=1.5,
areaRef=45.5,
chordRef=3.25,
evalFuncs=['cl', 'cd'])
#rst Create polar arrays
# Create an array of alpha values.
# In this case we create 6 evenly spaced values from 0 - 5.
alphaList = numpy.linspace(0, 5, 6)
class TestSolve(reg_test_classes.RegTest):
"""
Tests that ADflow can converge the wing from the mdo tutorial using the euler
equation to the required accuracy as meassure by the norm of the residuals,
and states, and the accuracy of the functions
based on the old regression test 15
"""
N_PROCS = 2
ref_file = "solve_rans_time_acc_naca0012.json"
def setUp(self):
super().setUp()
gridFile = os.path.join(baseDir,
"../../inputFiles/naca0012_rans-L2.cgns")
f = 10.0 # [Hz] Forcing frequency of the flow
period = 1.0 / f # [sec]
nStepPerPeriod = 8
nPeriods = 1
nfineSteps = nStepPerPeriod * nPeriods
dt = period / nStepPerPeriod # [s] The actual timestep
options = copy.copy(adflowDefOpts)
options.update({
"gridfile":
gridFile,
"outputdirectory":
os.path.join(baseDir, "../output_files"),
"writevolumesolution":
False,
"vis4":
0.025,
"vis2":
0.5,
"restrictionrelaxation":
0.5,
"smoother":
"dadi",
"equationtype":
"RANS",
"equationmode":
"unsteady",
"timeIntegrationscheme":
"bdf",
"ntimestepsfine":
nfineSteps,
"deltat":
dt,
"nsubiterturb":
10,
"nsubiter":
5,
"useale":
False,
"usegridmotion":
True,
"cfl":
2.5,
"cflcoarse":
1.2,
"ncycles":
2000,
"mgcycle":
"3w",
"mgstartlevel":
1,
"monitorvariables": ["cpu", "resrho", "cl", "cd", "cmz"],
"usenksolver":
False,
"l2convergence":
1e-6,
"l2convergencecoarse":
1e-4,
"qmode":
True,
"alphafollowing":
False,
"blockSplitting":
True,
"useblockettes":
False,
})
# Setup aeroproblem
self.ap = copy.copy(ap_naca0012_time_acc)
# Create the solver
self.CFDSolver = ADFLOW(options=options, debug=False)
self.CFDSolver.addSlices("z", [0.5])
def test_solve(self):
# do the solve
self.CFDSolver(self.ap)
# check its accuracy
utils.assert_functions_allclose(self.handler,
self.CFDSolver,
self.ap,
tol=1e-8)
def setup_cb(comm):
CFDSolver = ADFLOW(options=options, comm=comm)
CFDSolver.addSlices('z', [0.5])
CFDSolver(ap)
return CFDSolver, None, None, None
