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_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_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_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 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_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_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 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 test_DLLM_valid_dpLoads_distrib_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()
Post=DLLM.get_DLLMPost()
def f1(x):
OC.set_AoA_rad(x[0])
R=DLLM.comp_R(iAoA0)
DLLM.run_post()
func=Post.Lift_distrib
return func
def df1(x):
OC.set_AoA_rad(x[0])
R=DLLM.comp_R(iAoA0)
DLLM.run_post()
func_grad=Post.dpLift_distrib_dpAoA
N=len(func_grad)
np_func_grad=np.zeros((N,1))
np_func_grad[:,0]=func_grad[:]
return np_func_grad
def f2(x):
OC.set_AoA_rad(x[0])
R=DLLM.comp_R(iAoA0)
DLLM.run_post()
func=Post.Drag_distrib
return func
def df2(x):
OC.set_AoA_rad(x[0])
R=DLLM.comp_R(iAoA0)
DLLM.run_post()
func_grad=Post.dpDrag_distrib_dpAoA
N=len(func_grad)
np_func_grad=np.zeros((N,1))
np_func_grad[:,0]=func_grad[:]
return np_func_grad
val_grad1=FDValidGrad(2,f1,df1,fd_step=1.e-8)
ok1,df_fd1,df1=val_grad1.compare([AoA0],treshold=1.e-6,return_all=True)
val_grad2=FDValidGrad(2,f2,df2,fd_step=1.e-8)
ok2,df_fd2,df2=val_grad2.compare([AoA0],treshold=1.e-6,return_all=True)
norm1, norm2 = self.print_valid_FD([AoA0],'dpLift_distrib_dpAoA',df1,df_fd1,'dpDrag_distrib_dpAoA',df2,df_fd2)
self.plot_valid_FD([AoA0],'dpLift_distrib_dpAoA',df1,df_fd1,'dpDrag_distrib_dpAoA',df2,df_fd2, norm1, norm2, 'Loads_distrib_dpAoA')
if (ok1==True) and (ok2==True):
ok = True
else :
ok = False
assert(ok)
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 test_DLLM_valid_dpLoads_distrib_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()
Post=DLLM.get_DLLMPost()
def f1(x):
wing_param.update_from_x_list(x)
DLLM.set_geom(wing_param)
DLLM.comp_R(iAoA)
Post.run()
func=Post.Lift_distrib
return func
def df1(x):
wing_param.update_from_x_list(x)
DLLM.set_geom(wing_param)
DLLM.comp_R(iAoA)
Post.run()
func_grad=Post.dpLift_distrib_dpchi
return func_grad
def f2(x):
wing_param.update_from_x_list(x)
DLLM.set_geom(wing_param)
DLLM.comp_R(iAoA)
Post.run()
func=Post.Drag_distrib
return func
def df2(x):
wing_param.update_from_x_list(x)
DLLM.set_geom(wing_param)
DLLM.comp_R(iAoA)
Post.run()
func_grad=Post.dpDrag_distrib_dpchi
return func_grad
val_grad1=FDValidGrad(2,f1,df1,fd_step=1.e-8)
ok1,df_fd1,df1=val_grad1.compare(x0,treshold=1.e-6,return_all=True)
val_grad2=FDValidGrad(2,f2,df2,fd_step=1.e-8)
ok2,df_fd2,df2=val_grad2.compare(x0,treshold=1.e-6,return_all=True)
norm1, norm2 = self.print_valid_FD(x0,'dpLift_distrib_dpchi',df1,df_fd1,'dpDrag_distrib_dpchi',df2,df_fd2)
self.plot_valid_FD(x0,'dpLift_distrib_dpchi',df1,df_fd1,'dpDrag_distrib_dpchi',df2,df_fd2, norm1, norm2, 'Loads_distrib_dpchi')
if (ok1==True) and (ok2==True):
ok = True
else :
ok = False
assert(ok)
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 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 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 __init__(self, tag, wing_param, OC):
DLLMSolver.__init__(self, tag, wing_param, OC)
self.__N = self.get_wing_param().get_n_sect()
self.__ndv = self.get_wing_param().get_ndv()
self.__R_TL = numpy.zeros(self.__N+1)
self.__dpR_TL_dpW = numpy.zeros((self.__N+1,self.__N+1))
self.__dpR_TL_dpchi = numpy.zeros((self.__N+1,self.__ndv))
self.__dpF_list_dpW = None
self.__target_Lift = 10000.
# initialize the Newton-Raphson problem
self.__NRPb = None
self.__init_Newton_Raphson()
def test_DLLM_valid_dpR_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):
func=DLLM.comp_R(x)
return func
def df1(x):
func_grad=DLLM.comp_dpR_dpiAoA(x)
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 __init__(self, tag, geom, OC,verbose = 0, grad_active=True):
self.__verbose = verbose
DLLMSolver.__init__(self, tag, geom, OC, verbose = self.__verbose, grad_active=grad_active)
self.__N = self.get_geom().get_n_sect()
self.__ndv = self.get_geom().get_ndv()
self.__R_TL = numpy.zeros(self.__N+1)
self.__dpR_TL_dpW = numpy.zeros((self.__N+1,self.__N+1))
self.__dpR_TL_dpchi = numpy.zeros((self.__N+1,self.__ndv))
self.__dpF_list_dpW = None
self.__target_Lift = 0.
# initialize the Newton-Raphson problem
self.__NRPb = None
self.__init_Newton_Raphson()
def __init__(self, tag, wing_param, OC, verbose = 0):
self.__verbose = verbose
DLLMSolver.__init__(self, tag, wing_param, OC, verbose = self.__verbose)
self.__N = self.get_wing_param().get_n_sect()
self.__ndv = self.get_wing_param().get_ndv()
self.__R_TCl = numpy.zeros(self.__N+1)
self.__dpR_TCl_dpW = numpy.zeros((self.__N+1,self.__N+1))
self.__dpR_TCl_dpchi = numpy.zeros((self.__N+1,self.__ndv))
self.__dpF_list_dpW = None
self.__target_Cl = 0.5
# initialize the Newton-Raphson problem
self.__NRPb = None
self.__init_Newton_Raphson()
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 runDLLM(wing_param, OC):
DLLM = DLLMSolver('Wing',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_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_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 __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 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 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 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_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)
chords_eta = np.zeros(N+1)
rel_thicks_eta = np.zeros(N+1)
eta = np.zeros((3,N+1))
#-- set data
twist[:] = 0. # 0. twist for all sections
chords_eta[:] = 5. # 5m chord for all sections
rel_thicks_eta[:] = 0.15 # same rel_thick for all sections
sweep_eta[:] = sweep_rad
for i, r in enumerate(r_list):
abs_r = abs(r)
eta[0, i] = abs_r * span * np.sin(sweep_rad) + 0.25 * chords_eta[i]
eta[1, i] = r * span
wing_geom.set_twist(twist)
wing_geom.set_sweep_eta(sweep_eta)
wing_geom.set_chords_eta(chords_eta)
wing_geom.set_rel_thicks_eta(rel_thicks_eta)
wing_geom.set_eta(eta)
wing_geom.build_linear_airfoil(OC, AoA0=0.0, set_as_ref=True)
wing_geom.build_airfoils_from_ref()
wing_geom.update()
wing_geom.plot()
print wing_geom
DLLM = DLLMSolver('tuto3', wing_geom, OC, verbose=1, grad_active=False)
DLLM.run_direct()
DLLM.run_post()
DLLM.plot()
DLLM.export_F_list()
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
OC.set_humidity(0.)
OC.compute_atmosphere()
wing_param=Wing_Broken('broken_wing',n_sect=20)
wing_param.import_BC_from_file('input_parameters.par')
wing_param.build_linear_airfoil(OC, AoA0=0.0, set_as_ref=True)
wing_param.build_airfoils_from_ref()
wing_param.update()
print wing_param
thetaY0=wing_param.get_thetaY()
print 'thetaY0 shape',thetaY0.shape
print 'thetaY0=',thetaY0
DLLM = DLLMSolver('Simple',wing_param,OC)
DLLM.run_direct()
iAoA=DLLM.get_iAoA()
def f(x):
wing_param.set_thetaY(x)
DLLM.comp_R(iAoA)
DLLM.set_direct_computed()
DLLM.run_post()
func=DLLM.get_F_list()
return func
def df(x):
wing_param.set_thetaY(x)
DLLM.set_direct_computed()
DLLM.run_post()
OC.set_P0(101325.)
OC.set_humidity(0.)
OC.compute_atmosphere()
wing_param=Wing_Broken('broken_wing',n_sect=20)
wing_param.import_BC_from_file('input_parameters.par')
wing_param.build_linear_airfoil(OC, AoA0=0.0, set_as_ref=True)
wing_param.build_airfoils_from_ref()
wing_param.update()
wing_param.plot()
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 = Wing_param('test_param', geom_type='Broken', n_sect=20)
wing_param.build_wing()
wing_param.set_value('span', 34.1)
wing_param.set_value('sweep', 34.)
wing_param.set_value('break_percent', 33.)
wing_param.set_value('root_chord', 6.1)
wing_param.set_value('break_chord', 4.6)
wing_param.set_value('tip_chord', 1.5)
wing_param.set_value('root_height', 1.28)
wing_param.set_value('break_height', 0.97)
wing_param.set_value('tip_height', 0.33)
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', (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()
DLLM.run_post()
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_meta_airfoil(OC, '../MetaModelFixed.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
thetaY0=wing_param.get_thetaY()
print 'thetaY0 shape',thetaY0.shape
print 'thetaY0=',thetaY0
DLLM = DLLMSolver('Meta',wing_param,OC)
DLLM.run_direct()
iAoA=DLLM.get_iAoA()
def f(x):
wing_param.set_thetaY(x)
func=DLLM.comp_R(iAoA)
return func
def df(x):
wing_param.set_thetaY(x)
func_grad=DLLM.comp_dpR_dpthetaY()
return func_grad
val_grad=FDValidGrad(2,f,df,fd_step=1.e-9)
ok,df_fd,df=val_grad.compare(thetaY0,treshold=1.e-6,return_all=True)
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
x0=wing_param.get_dv_array()
DLLM = DLLMSolver('Simple',wing_param,OC)
DLLM.run_direct()
DLLM.run_post()
iAoA0=DLLM.get_iAoA()
AoA0=OC.get_AoA_rad()
def f(x):
OC.set_AoA_rad(x[0])
R=DLLM.comp_R(iAoA0)
# print 'x=',x
# print 'R=',R
# print 'iAoA updated?:',DLLM.get_iAoA()
Post=DLLM.get_DLLMPost()
func=Post.comp_Lift_distrib()
# print 'func=',func
import numpy
OC=OperatingCondition('cond1')
OC.set_Mach(0.8)
OC.set_AoA(3.5)
OC.set_altitude(10000.)
OC.set_T0_deg(15.)
OC.set_P0(101325.)
OC.set_humidity(0.)
OC.compute_atmosphere()
wing_param=Wing_Broken('broken_wing',n_sect=20)
wing_param.import_BC_from_file('input_parameters.par')
wing_param.build_linear_airfoil(OC, AoA0=0.0, set_as_ref=True)
wing_param.build_airfoils_from_ref()
wing_param.update()
wing_param.plot()
print wing_param
x0=wing_param.get_dv_array()
DLLM = DLLMSolver('Simple',wing_param,OC)
DLLM.run_direct()
DLLM.run_post()
Post=DLLM.get_DLLMPost()
print Post.dpLift_distrib_dpiAoA
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.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.set_value("sweep", 34.0)
wing_param.set_value("break_percent", 23.0) # 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", 0.98)
wing_param.set_value("break_height", 0.70)
wing_param.set_value("tip_height", 0.18)
wing_param.convert_to_design_variable("span", (10.0, 50.0))
wing_param.convert_to_design_variable("sweep", (0.0, 40.0))
wing_param.convert_to_design_variable("break_percent", (20.0, 40.0))
wing_param.convert_to_design_variable("root_chord", (5.0, 7.0))
wing_param.convert_to_design_variable("break_chord", (3.0, 5.0))
wing_param.convert_to_design_variable("tip_chord", (1.0, 2.0))
wing_param.convert_to_design_variable("root_height", (0.7, 1.0))
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=0.12, camber=0.0, Sref=1.0, Lref=1.0, sweep=0.0, 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()
DLLM.run_adjoint()
