摘要
采用保角变换与代数方法相结合，生成全场统一的贴体、正交Ｏ－Ｈ型网格．采用有限体积法求解Ｅｕｌｅｒ方程，模拟具有歼击机外形的全机及翼身组合体大迎角跨音速绕流．计算表明，法向力系数。
In this paper, the conformal mapping technique combined with the algebraic method is used, the unified body fitted orthonormal O H mesh is generated. The Euler equations are solved by finite volume method, the transonic flow about the fighter like aircraft and wing body configuration at high angles of attack can be simulated. The results of the computations show good agreement with experimental normal force coefficients, aerodynamic center position and surface pressure distributions.
出处
《力学学报》
EI
CSCD
北大核心
1996年第6期730-735,共6页
Chinese Journal of Theoretical and Applied Mechanics
基金
国防科工委85空气动力学预先性研究及国家教委博士点基金
关键词
大迎角
跨音速流
网格生成
飞行器
high angles of attack, transonic flow, mesh generation
