本文整理匯總了Python中DLLM.DLLMGeom.wing_param.Wing_param.build_meta_airfoil方法的典型用法代碼示例。如果您正苦於以下問題：Python Wing_param.build_meta_airfoil方法的具體用法？Python Wing_param.build_meta_airfoil怎麽用？Python Wing_param.build_meta_airfoil使用的例子？那麽, 這裏精選的方法代碼示例或許可以為您提供幫助。您也可以進一步了解該方法所在類DLLM.DLLMGeom.wing_param.Wing_param的用法示例。
在下文中一共展示了Wing_param.build_meta_airfoil方法的2個代碼示例，這些例子默認根據受歡迎程度排序。您可以為喜歡或者感覺有用的代碼點讚，您的評價將有助於係統推薦出更棒的Python代碼示例。
示例1: DLLMSolver
# 需要導入模塊: from DLLM.DLLMGeom.wing_param import Wing_param [as 別名]
# 或者: from DLLM.DLLMGeom.wing_param.Wing_param import build_meta_airfoil [as 別名]
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()
示例2: DLLMSolver
# 需要導入模塊: from DLLM.DLLMGeom.wing_param import Wing_param [as 別名]
# 或者: from DLLM.DLLMGeom.wing_param.Wing_param import build_meta_airfoil [as 別名]
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()