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) np_func_grad = numpy.zeros((N, 1)) np_func_grad[:, 0] = func_grad[:] return np_func_grad
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() print 'dv array shape',x0.shape print 'dv_array=',x0 DLLM = DLLMSolver('Simple',wing_param,OC) DLLM.run_direct() iAoA=DLLM.get_iAoA() AoA0=OC.get_AoA_rad() # Split validation in 2 steps since the norm depends on the function value scale... def f(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 df(x): OC.set_AoA_rad(x[0]) DLLM.comp_R(iAoA) DLLM.set_direct_computed() DLLM.run_post()