'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)