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 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)
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.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
x0 = wing_param.get_dv_array()
DLLM = DLLMSolver('Simple', wing_param, OC)
DLLM.run_direct()
DLLM.run_post()
Post = DLLM.get_DLLMPost()
dpLift_distrib_dpiAoA = Post.comp_dpLift_distrib_dpiAoA()
print dpLift_distrib_dpiAoA
