def test_setBCData(self):
"Test if bcdata is correctly set to data arrays"
CFDSolver = ADFLOW(options=self.options)
CFDSolver.addFamilyGroup('upstream',['inlet'])
CFDSolver.addFamilyGroup('downstream',['outlet'])
bc_data = CFDSolver.getBCData(groupNames=self.set_dvs.keys())
for patch in bc_data:
if patch.fam in self.set_dvs:
for arr in patch:
if arr.name in self.set_dvs[patch.fam]:
arr.data = self.set_dvs[patch.fam][arr.name]
CFDSolver.setBCData(bc_data)
# CFDSolver.setAeroProblem(self.ap)
new_bc_data = CFDSolver.getBCData(groupNames=self.set_dvs.keys())
## check that the mesh bc match
for patch in new_bc_data:
for arr in patch:
np.testing.assert_array_equal(arr.data,
np.array(self.set_dvs[patch.fam][arr.name])
, err_msg=arr.name)
def test_ap_bcvar_nodal_array(self):
gridFile = os.path.join(baseDir, '../input_files/conic_conv_nozzle_mb_L4_array.cgns')
options = copy.deepcopy(self.options)
options['gridfile'] = gridFile
CFDSolver = ADFLOW(options=options)
CFDSolver.addFamilyGroup('upstream',['inlet'])
CFDSolver.addFamilyGroup('downstream',['outlet'])
ap = self.ap
group = 'outlet'
BCVar = 'Pressure'
# ap.bc_data = bc_data
ap.setBCVar(BCVar, 70000.0, group)
ap.addDV(BCVar, name='outlet_pressure', familyGroup=group,)
# DVs = {'outlet_pressure':123000.0}
DVs = {'outlet_pressure':np.arange(1,5*9+1)*10**5}
ap.setDesignVars(DVs)
assert (ap.getBCData()[group][BCVar] == DVs['outlet_pressure']).all()
CFDSolver.setAeroProblem(ap)
bc_data = CFDSolver.getBCData(groupNames=[group])
for ii, d in enumerate(bc_data.getBCArraysFlatData(BCVar, familyGroup=group)):
assert d == DVs['outlet_pressure'][ii]
class BasicTests(unittest.TestCase):
N_PROCS = 1
def setUp(self):
gridFile = 'input_files/mdo_tutorial_euler.cgns'
options = {'gridfile': gridFile}
self.CFDSolver = ADFLOW(options=options)
def test_import(self):
"Tests if mesh was read properly"
nStates = self.CFDSolver.getStateSize()
assert (nStates == 60480)
def test_setBCData_array(self):
gridFile = os.path.join(baseDir, '../input_files/conic_conv_nozzle_mb_L4_array.cgns')
options = copy.deepcopy(self.options)
options['gridfile'] = gridFile
CFDSolver = ADFLOW(options=options)
CFDSolver.addFamilyGroup('upstream',['inlet'])
CFDSolver.addFamilyGroup('downstream',['outlet'])
bc_data = CFDSolver.getBCData(groupNames=self.set_dvs.keys())
for patch in bc_data:
if patch.fam in self.set_dvs:
for arr in patch:
if arr.name in self.set_dvs[patch.fam]:
arr.data = self.set_dvs[patch.fam][arr.name]*np.ones(arr.size)
CFDSolver.setBCData(bc_data)
bc_data = CFDSolver.getBCData(groupNames=self.set_dvs.keys())
for patch in bc_data:
for arr in patch:
np.testing.assert_array_equal(arr.data, np.ones(arr.size)*
self.set_dvs[patch.fam][arr.name])
def test_getBCData(self):
"Tests if mesh was read properly"
CFDSolver = ADFLOW(options=self.options)
CFDSolver.addFamilyGroup('upstream',['inlet'])
CFDSolver.addFamilyGroup('downstream',['outlet'])
bc_data = CFDSolver.getBCData(groupNames=self.initial_dvs.keys())
## check that the mesh bc match
for patch in bc_data:
for arr in patch:
np.testing.assert_array_equal(arr.data, np.array(self.initial_dvs[patch.fam][arr.name]))
def test_ap_bcvar_array(self):
CFDSolver = ADFLOW(options=self.options)
CFDSolver.addFamilyGroup('upstream',['inlet'])
CFDSolver.addFamilyGroup('downstream',['outlet'])
ap = self.ap
group = 'outlet'
BCVar = 'Pressure'
# ap.bc_data = bc_data
ap.setBCVar(BCVar, 70000.0, group)
ap.addDV(BCVar, name='outlet_pressure', familyGroup=group,)
# DVs = {'outlet_pressure':123000.0}
DVs = {'outlet_pressure':np.arange(1,6)*10**5}
ap.setDesignVars(DVs)
print(ap.getBCData()[group][BCVar] == DVs['outlet_pressure'])
assert (ap.getBCData()[group][BCVar] == DVs['outlet_pressure']).all()
CFDSolver.setAeroProblem(ap)
bc_data = CFDSolver.getBCData(groupNames=[group])
for ii, d in enumerate(bc_data.getBCArraysFlatData(BCVar, familyGroup=group)):
assert d == DVs['outlet_pressure'][ii]
def test_ap_bcvar_scalar(self):
CFDSolver = ADFLOW(options=self.options)
CFDSolver.addFamilyGroup('upstream',['inlet'])
CFDSolver.addFamilyGroup('downstream',['outlet'])
ap = self.ap
group = 'outlet'
BCVar = 'Pressure'
# ap.bc_data = bc_data
ap.setBCVar(BCVar, 70000.0, group)
ap.addDV(BCVar, name='outlet_pressure', familyGroup=group,)
DVs = {'outlet_pressure':123000.0}
ap.setDesignVars(DVs)
assert ap.getBCData()[group][BCVar] == DVs['outlet_pressure']
CFDSolver.setAeroProblem(ap)
bc_data = CFDSolver.getBCData(groupNames=[group])
for d in bc_data.getBCArraysFlatData(BCVar, familyGroup=group):
assert d == DVs['outlet_pressure']
def setUp(self):
gridFile = os.path.join(baseDir, '../input_files/pipe.cgns')
self.options = {'gridfile': gridFile,
'mgcycle':'sg',
'ncycles':1000,
'useanksolver':True,
'usenksolver':True,
'volumevariables': ['temp', 'mach', 'resrho' ],
'surfacevariables':['temp', 'vx', 'vy', 'vz', 'p', 'ptloss', 'mach', 'rho'],
'equationType':'euler',
'l2convergence': 1e-13}
CFDSolver = ADFLOW(options=self.options)
CFDSolver.addFunction('mdot', 'inlet', name="mdot_in")
CFDSolver.addFunction('mdot', 'outlet', name="mdot_out")
CFDSolver.addFunction('mavgptot', 'outlet', name="mavgptot_out")
CFDSolver.addFunction('mavgptot', 'inlet', name="mavgptot_in")
CFDSolver.addFunction('aavgptot', 'outlet', name="aavgptot_out")
CFDSolver.addFunction('aavgptot', 'inlet', name="aavgptot_in")
CFDSolver.addFunction('mavgttot', 'outlet', name="mavgttot_out")
CFDSolver.addFunction('mavgttot', 'inlet', name="mavgttot_in")
CFDSolver.addFunction('mavgps', 'outlet', name="mavgps_out")
CFDSolver.addFunction('mavgps', 'inlet', name="mavgps_in")
CFDSolver.addFunction('aavgps', 'outlet', name="aavgps_out")
CFDSolver.addFunction('aavgps', 'inlet', name="aavgps_in")
CFDSolver.addFunction('area', 'inlet', name="area_in")
CFDSolver.addFunction('area', 'outlet', name="area_out")
CFDSolver.addFunction('mavgvx', 'inlet', name="vx_in")
CFDSolver.addFunction('mavgvx', 'outlet', name="vx_out")
CFDSolver.addFunction('mavgps', 'inlet', name="ps_in")
CFDSolver.addFunction('mavgps', 'outlet', name="ps_out")
self.CFDSolver = CFDSolver
self.ap = AeroProblem(name='actuator_in_pipe', alpha=00, mach=0.6, altitude=0,
areaRef=1.0, chordRef=1.0,
evalFuncs=['mdot_in', 'mdot_out',
'mavgptot_in', 'mavgptot_out',
'mavgttot_in', 'mavgttot_out',
'mavgps_in', 'mavgps_out',
'area_in', 'area_out',
'aavgps_in', 'aavgps_out',
'aavgptot_in', 'aavgptot_out',
'ps_in', 'ps_out',
'vx_in', 'vx_out'] )
self.force = 600
actuatorFile = os.path.join(baseDir, '../input_files/actuator_disk.xyz')
self.CFDSolver.addActuatorRegion(actuatorFile, np.array([0,0,0]),np.array([1,0,0]), 'actuator', thrust=self.force )
def regression_test(self, handler, solve=False):
'''
This is where the actual testing happens.
'''
# gridFile = 'input_files/conic_conv_nozzle.cgns'
gridFile = '../python/inputFiles/conic_conv_nozzle.cgns'
options = copy.copy(adflowDefOpts)
options.update({
# Common Parameters
'gridfile':
gridFile,
# Physics Parameters
'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,
# Convergence Parameters
'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.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('mavgptot', 'downstream', name="mavgptot_down")
CFDSolver.addFunction('mavgptot', 'upstream', name="mavgptot_up")
CFDSolver.addFunction('aavgptot', 'downstream', name="aavgptot_down")
CFDSolver.addFunction('aavgptot', 'upstream', name="aavgptot_up")
CFDSolver.addFunction('mavgttot', 'downstream', name="mavgttot_down")
CFDSolver.addFunction('mavgttot', 'upstream', name="mavgttot_up")
CFDSolver.addFunction('mavgps', 'downstream', name="mavgps_down")
CFDSolver.addFunction('mavgps', 'upstream', name="mavgps_up")
CFDSolver.addFunction('aavgps', 'downstream', name="aavgps_down")
CFDSolver.addFunction('aavgps', 'upstream', name="aavgps_up")
CFDSolver.setOption('ncycles', 1000)
# Run test
# CFDSolver(ap)
# Check the residual
res = CFDSolver.getResidual(ap)
handler.par_add_norm(res, 1e-10, 1e-10, msg='res')
# Get and check the states
handler.par_add_norm(CFDSolver.getStates(), 1e-10, 1e-10, msg='states')
funcs = {}
CFDSolver.evalFunctions(ap, funcs)
handler.root_add_dict(funcs, 1e-10, 1e-10, msg='functions')
def regression_test(self, handler):
'''
This is where the actual testing happens.
'''
gridFile = 'input_files/euler_conv_nozzle.cgns'
options = copy.copy(adflowDefOpts)
options.update({
'gridfile': gridFile,
'equationType': 'euler',
'smoother': 'dadi',
'liftIndex': 2,
'CFL': 3.,
'CFLCoarse': 1.5,
'MGCycle': 'sg',
'MGStartLevel': 1,
'nCyclesCoarse': 500,
'nCycles': 2500,
'monitorvariables': ['resrho', 'cl', 'cd', 'yplus'],
'nsubiterturb': 3,
'useNKSolver': True,
'NKSubSpaceSize': 60,
'L2Convergence': 1e-14,
'L2ConvergenceCoarse': 1e-2,
'NKSwitchTol': 1e-2,
'nkadpc': False,
'vis4': 0.006,
'vis2': 0.0,
'blocksplitting': True,
'solutionPrecision': 'double',
'flowtype': 'internal',
'useblockettes': False
})
# Setup aeroproblem
ap = AeroProblem(
name='conv_nozzle',
alpha=00.0,
mach=0.25,
T=500,
P=79326.7,
areaRef=1.,
chordRef=2.,
R=287.87,
evalFuncs=[
'mdot', 'mdot_up', 'mdot_down', 'mavgptot_up', 'mavgptot_down',
'aavgptot_up', 'aavgptot_down', 'mavgttot_up', 'mavgttot_down',
'mavgps_up', 'mavgps_down', 'aavgps_up', 'aavgps_down',
'mavgmn_up', 'mavgmn_down', 'thrust', 'thrust_pressure',
'thrust_viscous', 'thrust_momentum'
])
# Create the solver
CFDSolver = ADFLOW(options=options)
CFDSolver.addFamilyGroup('upstream', ['INFLOW'])
CFDSolver.addFamilyGroup('downstream', ['OUTFLOW'])
CFDSolver.addFamilyGroup('all_flow', ['INFLOW', 'OUTFLOW'])
CFDSolver.addFunction('mdot', 'upstream', name="mdot_up")
CFDSolver.addFunction('mdot', 'downstream', name="mdot_down")
CFDSolver.addFunction('mavgptot', 'downstream', name="mavgptot_down")
CFDSolver.addFunction('mavgptot', 'upstream', name="mavgptot_up")
CFDSolver.addFunction('aavgptot', 'downstream', name="aavgptot_down")
CFDSolver.addFunction('aavgptot', 'upstream', name="aavgptot_up")
CFDSolver.addFunction('mavgttot', 'downstream', name="mavgttot_down")
CFDSolver.addFunction('mavgttot', 'upstream', name="mavgttot_up")
CFDSolver.addFunction('mavgps', 'downstream', name="mavgps_down")
CFDSolver.addFunction('mavgps', 'upstream', name="mavgps_up")
CFDSolver.addFunction('aavgps', 'downstream', name="aavgps_down")
CFDSolver.addFunction('aavgps', 'upstream', name="aavgps_up")
CFDSolver.addFunction('mavgmn', 'downstream', name="mavgmn_down")
CFDSolver.addFunction('mavgmn', 'upstream', name="mavgmn_up")
CFDSolver.addFunction(
'drag', 'all_flow',
name="thrust") # this naming makes it seem like wishful thinking
CFDSolver.addFunction('dragpressure',
'all_flow',
name="thrust_pressure")
CFDSolver.addFunction('dragviscous', 'all_flow', name="thrust_viscous")
CFDSolver.addFunction('dragmomentum',
'all_flow',
name="thrust_momentum")
# Run test
# CFDSolver.getResidual(ap)
CFDSolver(ap)
# Check the residual
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(self):
gridFile = 'input_files/mdo_tutorial_euler.cgns'
options = {'gridfile': gridFile}
self.CFDSolver = ADFLOW(options=options)
def setUp(self):
# import petsc4py
# petsc4py.init(arch='real-debug-gfortran-3.7.7')
# from petsc4py import PETSc
gridFile = os.path.join(baseDir, '../input_files/conic_conv_nozzle_mb_L4_array.cgns')
intSurfFile = os.path.join(baseDir, '../input_files/integration_plane_viscous.fmt')
self.options = {'gridfile': gridFile}
self.options['mgstartlevel'] = 1
self.options['mgstartlevel'] = 1
self.options['mgcycle'] = 'sg'
self.options['ncycles'] = 1
self.options['useanksolver'] = False
self.options['l2convergence'] = 1e-12
ap = AeroProblem(name='nozzle_flow', alpha=90, 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',
'mavgttot_up', 'mavgttot_down', 'mavgttot_plane',
'mavgps_up', 'mavgps_down', 'mavgps_plane',
])
self.ap = ap
CFDSolver = ADFLOW(options=self.options)
CFDSolver.addIntegrationSurface(intSurfFile, '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")
self.CFDSolver= CFDSolver
self.comm = MPI.COMM_WORLD
