def test_DLLM_valid_dpF_list_dpW(self):
OC, wing_param = self.__init_wing_param()
DLLM = DLLMSolver('test', wing_param, OC)
print ''
DLLM.run_direct()
iAoA0 = DLLM.get_iAoA()
def f1(x):
DLLM.comp_R(x)
DLLM.set_direct_computed()
DLLM.run_post()
func = DLLM.get_F_list()
return func
def df1(x):
DLLM.comp_R(x)
DLLM.set_direct_computed()
DLLM.run_post()
func_grad = DLLM.get_dpF_list_dpW()
return func_grad
val_grad1 = FDValidGrad(2, f1, df1, fd_step=1.e-8)
ok1, df_fd1, df1 = val_grad1.compare(iAoA0,
treshold=1.e-6,
return_all=True)
assert (ok1)
def f(x):
wing_param.update_from_x_list(x)
DLLM = DLLMSolver('Simple',wing_param,OC)
DLLM.run_direct()
DLLM.run_post()
func=DLLM.get_F_list()
return func
def test_DLLM_valid_dpF_list_dpchi(self):
OC, wing_param = self.__init_wing_param()
DLLM = DLLMSolver('test', wing_param, OC)
print ''
DLLM.run_direct()
iAoA = DLLM.get_iAoA()
x0 = wing_param.get_dv_array()
def f2(x):
wing_param.update_from_x_list(x)
DLLM.set_wing_param(wing_param)
DLLM.comp_R(iAoA)
DLLM.set_direct_computed()
DLLM.run_post()
func = DLLM.get_F_list()
return func
def df2(x):
wing_param.update_from_x_list(x)
DLLM.set_wing_param(wing_param)
DLLM.comp_R(iAoA)
DLLM.set_direct_computed()
DLLM.run_post()
func_grad = DLLM.get_dpF_list_dpchi()
return func_grad
val_grad2 = FDValidGrad(2, f2, df2, fd_step=1.e-8)
ok2, df_fd2, df2 = val_grad2.compare(x0,
treshold=1.e-6,
split_out=True,
return_all=True)
assert (ok2)
def test_DLLM_valid_dpF_list_dpAoA(self):
OC, wing_param = self.__init_wing_param()
DLLM = DLLMSolver('test', wing_param, OC)
print ''
DLLM.run_direct()
iAoA = DLLM.get_iAoA()
AoA0 = OC.get_AoA_rad()
def f3(x):
OC.set_AoA_rad(x[0])
DLLM.comp_R(iAoA)
DLLM.set_direct_computed()
DLLM.run_post()
func = DLLM.get_F_list()
return func
def df3(x):
OC.set_AoA_rad(x[0])
DLLM.comp_R(iAoA)
DLLM.set_direct_computed()
DLLM.run_post()
func_grad = DLLM.get_dpF_list_dpAoA()
N = len(func_grad)
np_func_grad = zeros((N, 1))
np_func_grad[:, 0] = func_grad[:]
return np_func_grad
val_grad3 = FDValidGrad(2, f3, df3, fd_step=1.e-8)
ok3, df_fd3, df3 = val_grad3.compare([AoA0],
treshold=1.e-6,
split_out=True,
return_all=True)
assert (ok3)
def test_DLLM_valid_dpLoads_dpAoA(self):
OC, wing_param = self.__init_wing_param()
DLLM = DLLMSolver('test', wing_param, OC)
print ''
DLLM.run_direct()
iAoA0 = DLLM.get_iAoA()
AoA0 = OC.get_AoA_rad()
def f2(x):
OC.set_AoA_rad(x[0])
R = DLLM.comp_R(iAoA0)
Post = DLLM.get_DLLMPost()
func = Post.comp_Lift_distrib()
return func
def df2(x):
OC.set_AoA_rad(x[0])
R = DLLM.comp_R(iAoA0)
Post = DLLM.get_DLLMPost()
func_grad = Post.comp_dpLift_distrib_dpAoA()
N = len(func_grad)
np_func_grad = zeros((N, 1))
np_func_grad[:, 0] = func_grad[:]
return np_func_grad
val_grad2 = FDValidGrad(2, f2, df2, fd_step=1.e-8)
ok2, df_fd2, df2 = val_grad2.compare([AoA0],
treshold=1.e-5,
return_all=True)
assert (ok2)
def test_DLLM_instantiation(self):
"""
test class instantiation
"""
OC, wing_param = self.__init_wing_param()
DLLM = DLLMSolver('test', wing_param, OC)
assert (DLLM is not None)
def f(x):
wing_param.update_from_x_list(x)
DLLM = DLLMSolver('Meta', wing_param, OC)
DLLM.run_direct()
#DLLM.run_post(func_list=['Cl'])
DLLM.run_post()
func = DLLM.get_F_list()
return func
def df(x):
wing_param.update_from_x_list(x)
DLLM = DLLMSolver('Simple',wing_param,OC)
DLLM.run_direct()
DLLM.run_post()
DLLM.run_adjoint()
func_grad=numpy.array(DLLM.get_dF_list_dchi())
return func_grad
def runDLLM(wing_param, OC):
DLLM = DLLMSolver('SimpleM6', wing_param, OC)
DLLM.run_direct()
DLLM.run_post()
output = DLLM.get_F_list()
F_list_names = DLLM.get_F_list_names()
return output, F_list_names
def test_DLLM_run_direct(self):
OC, wing_param = self.__init_wing_param()
DLLM = DLLMSolver('test', wing_param, OC)
try:
print ''
DLLM.run_direct()
ok = True
except:
ok = False
assert (ok)
def __config_DLLM(self):
WARNING_MSG=self.WARNING_MSG+'__config_DLLM: '
input_keys=self.__config_dict.keys()
type_key = self.__tag+'.DLLM.type'
type = self.__config_dict[type_key]
if type not in self.POS_SOLVER:
print WARNING_MSG+'solver_type = '+str(solve_type)+' not in '+str(self.POS_SOLVER)+'. Set to default solver_type = Solver'
type='Solver'
if type == 'Solver':
self.__DLLM_solver = DLLMSolver(self.__tag,self.__wing_param,self.__OC)
elif type == 'TargetCl':
self.__DLLM_solver = DLLMTargetCl(self.__tag,self.__wing_param,self.__OC)
target_Cl_key = self.__tag+'.DLLM.target_Cl'
target_Cl = self.__config_dict[target_Cl_key]
self.__DLLM_solver.set_target_Cl(target_Cl)
elif type == 'TargetLift':
self.__DLLM_solver = DLLMTargetLift(self.__tag,self.__wing_param,self.__OC)
target_Lift_key = self.__tag+'.DLLM.target_Lift'
target_Lift = self.__config_dict[target_Lift_key]
self.__DLLM_solver.set_target_Lift(target_Lift)
method_key = self.__tag+'.DLLM.method'
if method_key in input_keys:
method = self.__config_dict[method_key]
self.__DLLM_solver.set_method(method)
relax_factor_key = self.__tag+'.DLLM.relax_factor'
if relax_factor_key in input_keys:
relax_factor = self.__config_dict[relax_factor_key]
self.__DLLM_solver.set_relax_factor(relax_factor)
stop_residual_key = self.__tag+'.DLLM.stop_residual'
if stop_residual_key in input_keys:
stop_residual = self.__config_dict[stop_residual_key]
self.__DLLM_solver.set_stop_residual(stop_residual)
max_iterations_key = self.__tag+'.DLLM.max_iterations'
if max_iterations_key in input_keys:
max_iterations = self.__config_dict[max_iterations_key]
self.__DLLM_solver.set_max_iterations(max_iterations)
gamma_file_name_key = self.__tag+'.DLLM.gamma_file_name'
if gamma_file_name_key in input_keys:
gamma_file_name = self.__config_dict[gamma_file_name_key]
self.__DLLM_solver.set_gamma_file_name(gamma_file_name)
F_list_names_key = self.__tag+'.DLLM.F_list_names'
if F_list_names_key in input_keys:
F_list_names = self.__config_dict[F_list_names_key]
self.__DLLM_solver.set_F_list_names(F_list_names)
def test_DLLM_valid_dpR_dpthetaY(self):
OC,wing_param = self.__init_wing_param()
DLLM = DLLMSolver('test',wing_param,OC)
print ''
DLLM.run_direct()
iAoA=DLLM.get_iAoA()
thetaY0=wing_param.get_thetaY()
def f3(x):
wing_param.set_thetaY(x)
func=DLLM.comp_R(iAoA)
return func
def df3(x):
wing_param.set_thetaY(x)
func_grad=DLLM.comp_dpR_dpthetaY()
return func_grad
val_grad3=FDValidGrad(2,f3,df3,fd_step=1.e-8)
ok3,df_fd3,df3=val_grad3.compare(thetaY0,treshold=1.e-6,return_all=True)
assert(ok3)
def test_DLLM_valid_dpR_dpAoA(self):
OC,wing_param = self.__init_wing_param()
DLLM = DLLMSolver('test',wing_param,OC)
print ''
DLLM.run_direct()
iAoA = DLLM.get_iAoA()
AoA0=OC.get_AoA_rad()
def f4(x):
OC.set_AoA_rad(x[0])
func=DLLM.comp_R(iAoA)
return func
def df4(x):
OC.set_AoA_rad(x[0])
func_grad=DLLM.comp_dpR_dpAoA()
N=len(func_grad)
np_func_grad=zeros((N,1))
np_func_grad[:,0]=func_grad[:]
return np_func_grad
val_grad4=FDValidGrad(2,f4,df4,fd_step=1.e-8)
ok4,df_fd4,df4=val_grad4.compare([AoA0],treshold=1.e-6,return_all=True)
assert(ok4)
def test_DLLM_valid_dpLoads_dpiAoA(self):
OC, wing_param = self.__init_wing_param()
DLLM = DLLMSolver('test', wing_param, OC)
print ''
DLLM.run_direct()
iAoA0 = DLLM.get_iAoA()
def f1(x):
R = DLLM.comp_R(x)
Post = DLLM.get_DLLMPost()
func = Post.comp_Lift_distrib()
return func
def df1(x):
R = DLLM.comp_R(x)
Post = DLLM.get_DLLMPost()
func_grad = Post.comp_dpLift_distrib_dpiAoA()
return func_grad
val_grad1 = FDValidGrad(2, f1, df1, fd_step=1.e-8)
ok1, df_fd1, df1 = val_grad1.compare(iAoA0,
treshold=1.e-2,
return_all=True)
assert (ok1)
wing_param.convert_to_design_variable('span', (0., 50.))
wing_param.convert_to_design_variable('sweep', (0., 40.))
wing_param.convert_to_design_variable('break_percent', (20., 40.))
wing_param.convert_to_design_variable('root_chord', (5., 7.))
wing_param.convert_to_design_variable('break_chord', (3., 5.))
wing_param.convert_to_design_variable('tip_chord', (1., 2.))
wing_param.convert_to_design_variable('root_height', (1., 1.5))
wing_param.convert_to_design_variable('break_height', (0.8, 1.2))
wing_param.convert_to_design_variable('tip_height', (0.2, 0.5))
wing_param.build_linear_airfoil(OC, AoA0=-2., Cm0=-0.1, set_as_ref=True)
wing_param.build_airfoils_from_ref()
wing_param.update()
print wing_param
DLLM = DLLMSolver('Simple', wing_param, OC)
DLLM.run_direct()
iAoA0 = DLLM.get_iAoA()
AoA0 = OC.get_AoA_rad()
def f(x):
OC.set_AoA_rad(x[0])
func = DLLM.comp_R(iAoA0)
return func
def df(x):
OC.set_AoA_rad(x[0])
func_grad = DLLM.comp_dpR_dpAoA()
N = len(func_grad)
wing_param.convert_to_design_variable('root_chord', (5., 7.))
wing_param.convert_to_design_variable('break_chord', (3., 5.))
wing_param.convert_to_design_variable('tip_chord', (1., 2.))
wing_param.convert_to_design_variable('root_height', (1., 1.5))
wing_param.convert_to_design_variable('break_height', (0.8, 1.2))
wing_param.convert_to_design_variable('tip_height', (0.2, 0.5))
wing_param.build_linear_airfoil(OC, AoA0=-2., Cm0=-0.1, set_as_ref=True)
wing_param.build_airfoils_from_ref()
wing_param.update()
print wing_param
N = wing_param.get_n_sect()
iAoA0 = numpy.zeros(N)
DLLM = DLLMSolver('test', wing_param, OC)
NRPb = NewtonRaphsonProblem(iAoA0, DLLM.comp_R, DLLM.comp_dpR_dpiAoA)
NRPb.set_relax_factor(0.99)
NRPb.set_stop_residual(1.e-9)
NRPb.set_max_iterations(100)
iAoA = NRPb.solve()
DLLM.set_direct_computed()
print iAoA
DLLM.comp_dpR_dpchi()
dpRdpthetaY = DLLM.comp_dpR_dpthetaY()
print 'dpRdpthetaY=', dpRdpthetaY
wing_param.build_wing()
wing_param.set_value('span',34.1) #34.1
wing_param.set_value('sweep',34.)
wing_param.set_value('break_percent',23.) #33.
wing_param.set_value('root_chord',5.4) #6.1
wing_param.set_value('break_chord',4.6)
wing_param.set_value('tip_chord',1.2) #1.5
wing_param.set_value('root_height',.98)
wing_param.set_value('break_height',0.70)
wing_param.set_value('tip_height',0.18)
wing_param.convert_to_design_variable('span',(10.,50.))
wing_param.convert_to_design_variable('sweep',(0.,40.))
wing_param.convert_to_design_variable('break_percent',(20.,40.))
wing_param.convert_to_design_variable('root_chord',(5.,7.))
wing_param.convert_to_design_variable('break_chord',(3.,5.))
wing_param.convert_to_design_variable('tip_chord',(1.,2.))
wing_param.convert_to_design_variable('root_height',(0.7,1.))
wing_param.convert_to_design_variable('break_height',(0.45,0.8))
wing_param.convert_to_design_variable('tip_height',(0.10,0.26))
#wing_param.build_linear_airfoil(OC, AoA0=-2., Cm0=-0.1, set_as_ref=True)
wing_param.build_meta_airfoil(OC, '../MetaModelCleaning.xml', relative_thickness=.12, camber=0., Sref=1., Lref=1., sweep=.0, set_as_ref=True)
wing_param.build_airfoils_from_ref()
wing_param.update()
print wing_param
DLLM = DLLMSolver('Meta',wing_param,OC)
DLLM.run_direct()
DLLM.run_post()
wing_param.set_value('root_height', 0.0782)
wing_param.set_value('break_height', 0.0668)
wing_param.set_value('tip_height', 0.0438)
wing_param.convert_to_design_variable('span', (10., 50.))
wing_param.convert_to_design_variable('sweep', (0., 40.))
wing_param.convert_to_design_variable('break_percent', (20., 40.))
wing_param.convert_to_design_variable('root_chord', (5., 7.))
wing_param.convert_to_design_variable('break_chord', (3., 5.))
wing_param.convert_to_design_variable('tip_chord', (1., 2.))
wing_param.convert_to_design_variable('root_height', (0.7, 1.))
wing_param.convert_to_design_variable('break_height', (0.45, 0.8))
wing_param.convert_to_design_variable('tip_height', (0.10, 0.26))
wing_param.build_linear_airfoil(OC, AoA0=-2., Cm0=-0.1, set_as_ref=True)
wing_param.build_meta_airfoil(OC,
'../ONERA_D.xml',
relative_thickness=.0,
camber=0.,
Sref=1.,
Lref=1.,
sweep=.0,
set_as_ref=True)
wing_param.build_airfoils_from_ref()
wing_param.update()
print wing_param
DLLM = DLLMSolver('M6wing', wing_param, OC)
DLLM.run_direct()
DLLM.run_post()
#DLLM.run_adjoint()
