高超声速三维化学非平衡流动简化NS方程数值解  

NUMERICAL SOLUTION OF SIMPLIFIED NAVIER-STOKES EQUATIONS FOR HYPERSONIC THREE-DIMENSIONAL VISCOUS FLOWS WITH CHEMICAL NONEQUILIBRIUM

作　　者：欧阳水吾[1] 苏玉宏[1] 谢中强[1] 

机构地区：[1]北京空气动力研究所

出　　处：《力学学报》1994年第4期385-396,共12页Chinese Journal of Theoretical and Applied Mechanics

摘　　要：本文研究用时间稳定法求解高超声速三维化学非平衡流动简化ＮＳ方程，把整个非平衡流体动力学问题分裂为流体力学问题和化学问题。流体力学与化学问题之间的耦合通过迭代方式加以处理。考虑高温空气分解与电离，七个化学组元，并认为化学反应是以有限速率进行的．差分格式采用无自由参数的混合反扩散格式，激波及壁面处理应用特征线理论．对来流攻角为１０°，马赫数为２６，飞行高度为８５ｋｍ的钝锥体，给出了流场参数和物面加热率的数值计算结果．In this paper the time-dependent method has been applied to the compu-tation of simplified Navier-Stokes equations for hypersonic three-dimensional viscous flowswith chemical nonequilibrium. The overall problem is decoupled into(a)a fluid mechanicproblem and(b)a chemistry problem. The coupling between the fluid mechanics and thechemistry is treated in an iterative manner. For very high Mach number the air in the shocklayer that envelops the body is at high temperature. The air may become appreciably dis- sociated and ionized. The degree of chemical reaction and ionization can have a significantaffect on the nature of the flowfield. For the chmistry problem a seven species gas model hasbeen applied to represent the finite rate chemically reacting air mixture. Zhang’s mixing-anti-diffusing difference scheme without free parameter flux is used.The shock and surfaceboundary conditions are treated using flow charactristic theory. Computation is performedfor the flowfield around a blunt cone reentry configuration at Mach 26,a flight altitudeof 85km and 10 degree angle of attack. Numerical results are obtained for the flowfieldparameters and surface heat transfer rates.

关 键 词：化学非平衡 空气动力学 高超音速 

分 类 号：V211.22[航空宇航科学与技术—航空宇航推进理论与工程]