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�������պ����ѧѧ�� 2008, Vol. 34 Issue (04) :417-421    DOI:
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���Ļ�, ��Ρ, �߸�*
�������պ����ѧ ���շ��������������ص�ʵ����, ���� 100083
Numerical simulation of airfoil transonic viscous flow using GAO-YONG turbulence model
Yan Wenhui, Yan Wei, Gao Ge*
National Key Laboratory on Aero-Engines, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

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Abstract�� Numerical simulation of transonic viscous flow around NACA0012 airfoil and RAE2822 airfoil based on Gao-Yong compressible turbulence model were presented. The convection term and the diffusion term were discretized by the third-order ROE scheme and the second-order center difference(CD) scheme respectively. The Runge-Kutta time marching method was applied to solve the space discrete control equations. The calculations accurately predict distribution of pressure coefficient on the airfoil surface, location of shock wave and distribution of contour of the Mach number. Shock-wave/boundary layer interaction and translation from the laminar flow to the turbulence flow on the airfoil surface were analyzed. The numerical results agree with the experimental data very well. The results demonstrate that Gao-Yong compressible turbulence model has a powerful capability to accurately simulate transonic viscous flow around the airfoil. A method for forecasting location of translation based on theory of orthotropic turbulence viscosity in the Gao-Yong compressible turbulence model was presented.
Keywords�� compressible flow   Gao-Yong turbulence model   shock waves   transonic flow   boundary layer     
Received 2007-03-30;
About author: ���Ļ�(1979-),��,����ͨ����,��ʿ��,abuaa@sjp.buaa.edu.cn.
���Ļ�, ��Ρ, �߸�.��GAO-YONG����ģʽ�����Ϳ���ճ������ֵģ��[J]  �������պ����ѧѧ��, 2008,V34(04): 417-421
Yan Wenhui, Yan Wei, Gao Ge.Numerical simulation of airfoil transonic viscous flow using GAO-YONG turbulence model[J]  JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2008,V34(04): 417-421
http://bhxb.buaa.edu.cn//CN/     ��     http://bhxb.buaa.edu.cn//CN/Y2008/V34/I04/417
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