摘要
应用有限体积法求解Ｅｕｌｅｒ方程计算了真实飞机外形的跨音速大迎角绕流流场及空气动力特性。本方法能自动捕获大后掠机翼前缘脱体涡，侧缘涡，机身体涡以及它们间的相互干扰。计算的机翼压力分布及全机气动力系数与实验值符合良好。表明了本文所采用的计算网格生成技术及流场计算方法是有效、可行的。
In this paper, the conformal mapping technique combined with the algebraic method is used to generate the unified body fitted orthonormal O H mesh for fighter type aircraft. The flow field and aerodynamic characteristics of complete aircrafts transonic flow at angles of attack have been successfully calculated by applying finite volume method to solved the Euler equations with high efficiency. The feasibility of using solution of Euler equations to simulate separated flow at high angles of attack is discussed. The calculation shows that the method described here can automatically capture highly swept back wing leading edge separated flow vortices, body vortices, horizontal tail tip vortices and their mutual interactions. The results of calculation are in good agreement with experimental data of wing surface pressure distributions and aerodynamic characteristic for complete aircraft.
出处
《应用力学学报》
CAS
CSCD
北大核心
1997年第3期34-39,共6页
Chinese Journal of Applied Mechanics
关键词
飞机
计算流体力学
跨音速
大迎角
Euler equations, aircraft, computational fluid dynamics.
