跨音速大迎角绕流的Euler方程数值模拟

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、气动中心位置及压力分布的计算结果与实验结果吻合良好

NUMERICAL SOLUTION OF THE EULER EQUATIONS FOR THE TRANSONIC FLOW ABOUT THE COMPLETE AIRCRAFT AT HIGH ANGLES OF ATTACKE

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.