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()