计算机翼跨音速绕流的加罚Galerkin有限元法  

A PENALTY-GALERKIN FINITE ELEMENT METHOD FOR CALCULATING TRANSONIC FLOW OVER WINGS

作　　者：张庆兵[1] 俞守勤[1] 

机构地区：[1]南京航空学院

出　　处：《航空学报》1991年第3期A193-A197,共5页Acta Aeronautica et Astronautica Sinica

摘　　要：1.引言 全速位Galerkin有限元法是跨音速有限元法中重要方法之一。处理超临界流时,为了自动捕捉到激波,通常采用上风技术,但因此导致了质量守恒条件得不到完全满足。文献[1]从Bateman变分原理出发,应用加罚函数方法,找出了强制满足质量守恒条件在Galerkin有限元方程中所应加入的附加项。本文将文献[1]的方法应用到超临界跨音速绕机翼流动。An upwind technique is usually used in order to capture the shocks in the (Jalerkm full potential finite element method for calculating supercritical transonic flows. But it leads to the vibration of the equation of mass conservation. The present formulation extends the Galerkin finite element method by modifying it with penalty function to enforce the conservation of mass across the element interfaces, while allowing sudden changes in velocities and densities in 2-D transonic flows over airfoils. The algorithm is then extended to over three-dimentional wings.

关 键 词：跨音速流 全速位方程 机翼 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程]