def twist(val, geo): for i in range(nTwist): geo.rot_z['wing'].coef[i] = val[i] def span(val, geo): # Span C = geo.extractCoef('wing') s = geo.extractS('wing') for i in range(len(C)-1): C[-1, 2] = C[-1, 2] + val[0] geo.restoreCoef(C, 'wing') DVGeo.addGeoDVGlobal('twist', [0]*nTwist, twist, lower=-10, upper=10, scale=1.0) DVGeo.addGeoDVGlobal('span', [0], span, lower=-10, upper=10, scale=1.0) DVGeo.addGeoDVLocal('shape', lower=-0.5, upper=0.5, axis='y', scale=10.0) mesh = MBMesh(options={'gridFile':'../inputFiles/mdo_tutorial_euler.cgns'}) CFDSolver.setMesh(mesh) CFDSolver.setDVGeo(DVGeo) #Aeroproblem must be set before we can call DVGeo.setDesignVars CFDSolver.setAeroProblem(ap) if not 'complex' in sys.argv: # Solve system CFDSolver(ap, writeSolution=False) funcs = {} CFDSolver.evalFunctions(ap, funcs) # Solve sensitivities funcsSens = {} CFDSolver.evalFunctionsSens(ap, funcsSens) # Write values and derivatives out: if MPI.COMM_WORLD.rank == 0:
# Adjoint Parameters 'adjointL2Convergence': 1e-6, 'adjointMaxIter': 2000, } meshOptions = { 'gridFile': gridFile, 'warpType': 'algebraic', } # Create solver CFDSolver = ADFLOW(options=aeroOptions, comm=comm) # Set up mesh warping mesh = MBMesh(options=meshOptions, comm=comm) CFDSolver.setMesh(mesh) CFDSolver.setDVGeo(DVGeo) # ============================================================================== # Set up structural analysis # ============================================================================== structOptions = { 'gravityVector': [0, -9.81, 0], 'projectVector': [0, 1, 0], # normal to planform } # Set up TACS on the struct proc FEASolver = pytacs.pyTACS('wingbox.bdf', comm=comm, options=structOptions) FEASolver.setDVGeo(DVGeo) execfile('INPUT/setup_structure.py')
# Solution Parameters 'nSolutionSteps': 5, # only for nonLinear or steppedLinear 'ksp_its': 25, 'warp_tol': 1e-10, # overall tolerance for nonLinear/steppedLinear 'reduction_factor_for_reform': 0.5, 'useSolutionMonitor': False, 'useKSPMonitor': False, # Physical parameters 'nu': 0.0, 'e_exp': 1.0, 'skew_exp': 0.0, 'useRotationCorrection': False, } mesh = MBMesh(options=optMesh) options.update({ 'gridfile': '../inputFiles/naca0012_rans-L2.cgns', 'writevolumesolution': False, 'vis4': .025, 'vis2': 0.5, 'restrictionrelaxation': .5, 'smoother': 'dadi', 'equationtype': 'RANS', 'equationmode': 'unsteady', 'timeIntegrationscheme': 'bdf', 'ntimestepsfine': nfineSteps, 'deltat': dt, 'nsubiterturb': 10, 'nsubiter': 5,
# Solution Parameters 'nSolutionSteps': 5, # only for nonLinear or steppedLinear 'ksp_its': 25, 'warp_tol': 1e-10, # overall tolerance for nonLinear/steppedLinear 'reduction_factor_for_reform': 0.5, 'useSolutionMonitor': False, 'useKSPMonitor': False, # Physical parameters 'nu': 0.0, 'e_exp': 1.0, 'skew_exp': 0.0, 'useRotationCorrection': False, } # Create mesh object mesh0 = MBMesh(options=meshOptions) mesh_vec = [] for i in xrange(ntimeintervalsspectral): mesh_vec.append(MBMesh(options=meshOptions)) # ====================================================================== # CFD INPUTS # ====================================================================== MGCycle = '2w' name = 'aero_struct' aeroOptions = { # Common Parameters 'gridFile': gridFile, 'outputDirectory': 'OUTPUT',
def test6(): # **************************************************************************** printHeader('MDO tutorial RANS Geometric Variables') # **************************************************************************** aeroOptions = copy.deepcopy(defOpts) # Now set the options that need to be overwritten for this example: aeroOptions.update( {'gridfile': '../inputFiles/mdo_tutorial_rans.cgns', 'mgcycle':'2w', 'equationtype':'RANS', 'smoother':'dadi', 'nsubiterturb':3, 'nsubiter':3, 'cfl':1.5, 'cflcoarse':1.25, 'ncyclescoarse':250, 'ncycles':750, 'monitorvariables':['resrho','resturb','cl','cd','cmz','yplus','totalr'], 'usenksolver':True, 'l2convergence':1e-17, 'l2convergencecoarse':1e-2, 'nkswitchtol':1e-4, 'adjointl2convergence': 1e-16, 'nkls': 'non monotone', 'frozenturbulence':False, 'nkjacobianlag':2, } ) # Setup aeroproblem, cfdsolver ap = AeroProblem(name='mdo_tutorial', alpha=1.8, mach=0.80, altitude=10000.0, areaRef=45.5, chordRef=3.25, evalFuncs=['cl','cmz','drag']) ap.addDV('alpha') ap.addDV('mach') CFDSolver = ADFLOW(options=aeroOptions) if 'complex' in sys.argv: DVGeo = DVGeometry('../inputFiles/mdo_tutorial_ffd.fmt', complex=True) else: DVGeo = DVGeometry('../inputFiles/mdo_tutorial_ffd.fmt', complex=False) nTwist = 2 DVGeo.addRefAxis('wing', pyspline.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 xrange(nTwist): geo.rot_z['wing'].coef[i] = val[i] def span(val, geo): # Span C = geo.extractCoef('wing') s = geo.extractS('wing') for i in xrange(len(C)-1): C[-1, 2] = C[-1, 2] + val[0] geo.restoreCoef(C, 'wing') DVGeo.addGeoDVGlobal('twist', [0]*nTwist, twist, lower=-10, upper=10, scale=1.0) DVGeo.addGeoDVGlobal('span', [0], span, lower=-10, upper=10, scale=1.0) DVGeo.addGeoDVLocal('shape', lower=-0.5, upper=0.5, axis='y', scale=10.0) mesh = MBMesh(options={'gridFile':'../inputFiles/mdo_tutorial_rans.cgns'}) CFDSolver.setMesh(mesh) CFDSolver.setDVGeo(DVGeo) #Aeroproblem must be set before we can call DVGeo.setDesignVars CFDSolver.setAeroProblem(ap) if not 'complex' in sys.argv: # Solve system CFDSolver(ap, writeSolution=False) funcs = {} CFDSolver.evalFunctions(ap, funcs) # Solve sensitivities funcsSens = {} CFDSolver.evalFunctionsSens(ap, funcsSens) # Write values and derivatives out: if MPI.COMM_WORLD.rank == 0: for key in ['cl','cmz','drag']: print 'funcs[%s]:'%key reg_write(funcs['mdo_tutorial_%s'%key],1e-10,1e-10) # Now write the derivatives in the same order the CS will do them: print ('Twist[0] Derivatives:') reg_write(funcsSens['mdo_tutorial_cl']['twist'][0][0], 1e-10,1e-10) reg_write(funcsSens['mdo_tutorial_cmz']['twist'][0][0], 1e-10,1e-10) reg_write(funcsSens['mdo_tutorial_drag']['twist'][0][0], 1e-10,1e-10) print ('Span Derivatives:') reg_write(funcsSens['mdo_tutorial_cl']['span'][0], 1e-10,1e-10) reg_write(funcsSens['mdo_tutorial_cmz']['span'][0], 1e-10,1e-10) reg_write(funcsSens['mdo_tutorial_drag']['span'][0], 1e-10,1e-10) print ('shape[13] Derivatives:') reg_write(funcsSens['mdo_tutorial_cl']['shape'][0][13], 1e-10,1e-10) reg_write(funcsSens['mdo_tutorial_cmz']['shape'][0][13], 1e-10,1e-10) reg_write(funcsSens['mdo_tutorial_drag']['shape'][0][13], 1e-10,1e-10) print ('mach Derivatives:') reg_write(funcsSens['mdo_tutorial_cl']['mach_mdo_tutorial'], 1e-10,1e-10) reg_write(funcsSens['mdo_tutorial_cmz']['mach_mdo_tutorial'], 1e-10,1e-10) reg_write(funcsSens['mdo_tutorial_drag']['mach_mdo_tutorial'], 1e-10,1e-10) else: # For the complex....we just do successive perturbation for ii in range(4): xRef = {'twist':[0.0, 0.0], 'span':[0.0], 'shape':numpy.zeros(72, dtype='D'), 'mach_mdo_tutorial':0.8} if ii == 0: xRef['twist'][0] += h*1j elif ii == 1: xRef['span'][0] += h*1j elif ii == 2: xRef['shape'][13] += h*1j else: xRef['mach_mdo_tutorial']+=h*1j ap.setDesignVars(xRef) CFDSolver.resetFlow(ap) DVGeo.setDesignVars(xRef) CFDSolver(ap, writeSolution=False) funcs = {} CFDSolver.evalFunctions(ap, funcs) if MPI.COMM_WORLD.rank == 0: if ii == 0: for key in ['cl','cmz','drag']: print 'funcs[%s]:'%key reg_write(numpy.real(funcs['mdo_tutorial_%s'%key]),1e-10,1e-10) if ii == 0: print ('Twist[0] Derivatives:') elif ii == 1: print ('Span Derivatives:') elif ii == 2: print ('shape[13] Derivatives:') elif ii == 3: print ('mach Derivatives:') for key in ['cl','cmz','drag']: deriv = numpy.imag(funcs['mdo_tutorial_%s'%key])/h reg_write(deriv,1e-10,1e-10) del CFDSolver del mesh