def __init_wing_param(self): 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_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_meta_airfoil(OC, '../examples/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() return OC, wing_param
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()
wing_param.build_wing() wing_param.set_value('span',2.392) #34.1 wing_param.set_value('sweep',26.7) wing_param.set_value('break_percent',33.) #33. wing_param.set_value('root_chord',0.806) #6.1 wing_param.set_value('break_chord',0.689) wing_param.set_value('tip_chord',0.451) #1.5 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()
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()