摘要
本文用一个单步二阶精度格式,对由物体截面突变引起的二维超声速分离流动进行了数值模拟。计算了近尾迹流场,并详细研究了来流M数和Re数对绕后台阶分离流场结构的影响,得到了与理论和前人计算一致的结果。另外,对超声速绕竖舨流动进行了数值计算,给出了细致的流场结构图画。
In this paper, the 2-D separated flows caused by suddenly change of the body section was studied with numerical solution of N-S equations. The differential equations were approximated with a one-step, two-order finite difference scheme developed in ref. [1-2]. Firstly, near wake flow was calculated. Secondly, the effect of Mach and Reynolds number of free stream on the flows around backward step was researched. The results agreed with theory and the data from other calculations. Finially, the flow field around a plate monuted perpendicularly on a flat plate was simulated, and details of flow structure was obtained clearly.
出处
《空气动力学学报》
CSCD
北大核心
1991年第4期402-409,共8页
Acta Aerodynamica Sinica
关键词
分离流
N-S方程
数值模拟
飞行器
separated flows, N-S equations, numerical simulation.
