摘要
本文利用格林定理将全速位方程转换为全速位积分方程，应用高斯定理对沿激波面的显式积分进行简化。将全速位积分方程的解表示成为面元项和场元项之和，然后离散进行数值求解。本文将激波捕捉方法和激波装配技术结合起来，对机翼跨声速绕流进行数值实验，计算结果令人满意。
An integral equation method to solve the full potential equation for calculating transonic flow over wings is formulated in this paper. The Green's theorem is used to transform the full potential equation to an integral equation. The integral equation is expressed in field and pannel terms.Discretion of this equation is solved by an iterative pro-cedure with the shock-capturing and shock-fitting techniques.The compu-tation results are in agreement with those received by other methods.
出处
《空气动力学学报》
CSCD
北大核心
1994年第4期391-397,共7页
Acta Aerodynamica Sinica
关键词
跨声速流动
积分方程
机翼
空气动力学
Transonic flow, integral equation, full potential equa-tion shock-capturing,shock-fitting.
