关于飞行器高超声速不平衡气体绕流的数值模拟  

ON THE MATHEMATICAL SIMULATION OF NONEQUILIBRIUM HYPERSONIC FLOW AROUND THE FLYING VEHICLE

作　　者：范绪箕[1] 

机构地区：[1]上海交通大学机械与动力学院,上海200030

出　　处：《力学进展》2004年第2期224-236,共13页Advances in Mechanics

摘　　要：高速飞行器气动计算是伴随着计算机技术及空气动力学的发展而发展的。较早从宏观角度出发求解欧拉方程,N-S方程,到考虑真实气体影响带化学反应和电离的N-S方程的求解,以及从微观角度出发用蒙特卡洛法对气体分子运动直接模拟求解(DSMC),即代表计算动力学理论的发展,也是计算机技术发展的结果。虽然从理论上说DSMC方法适用于各种流动,但所需的计算时间非常巨大,因此只在不可避免的情况下才会应用,否则仍用宏观的解决方法。本文讨论的是与气动热有关的高超声速飞行问题,包括数学模型的选择,空气化学组分的确定及其化学反应,边界条件处理,辐射热的计算等等,最后推荐如何正确选择高超声速飞行的数学模拟方法。The Computational Fluid Dynamics of high-speed flight is developing in parallel with the computer technology.In treating the problem macroscopically, the ordinary way of solving the Euler equations and N-S equations is improved to account for the real gas effect, which means including chemical reactions and ionization of the gas particles. Microscopically, treating the problem by Monte-Carlo method to simulate the motion of gas particles(DSMC) is also developed. Although theoretically the DSMC method is applicable to all kinds of flow, the computer time required for computation is enormous, therefore, it is only used in special cases and the macroscopic method is mostly used. This paper discusses the hypersonic flight problems related to the aerodynamic heating, including the choice of the mathematical model, the determination of chemical species and their reactions, the treatment of boundary conditions, the calculation of the heat generated by radiation and so forth. Finally, the proper way of mathematical simulation of hypersonic flight is proposed.

关 键 词：飞行器 气动加热 真实气体效应 化学反应 化学组份 数值模拟 绕流 

分 类 号：V47[航空宇航科学与技术—飞行器设计] V211