摘要
进气道是航空推进系统的一个重要组成部分,进气道内的流场品质会显著影响发动机的性能。由于进气道内部流动的复杂性和其广泛的应用前景,进气道内的流动特性引起了人们广泛的关注。采用计算流体力学(CFD)方法,空间离散采用Harten-Yee的二阶迎风TVD格式,时间迭代采用隐式LU-SGS方法,数值求解Navier-Stokes(N-S)方程,对进气道内部流场进行了数值模拟,并研究了进气道内部流场的流场结构以及激波/边界层干扰问题。数值计算结果反映出了流场的基本物理现象,说明了所采用的研究方法是可行的。同时数值模拟结果对进气道的设计有一定的参考价值。
As a crucial part in space flight and aviation propulsive system, the flow quality in the supersonic inlet will remarkably influence engine＇s performance. The phenomenon of flow fields in supersonic inlet has broadly drawn people＇s attention due to both the complexity in aerodynamics and its wide engineering applications. In this paper, the flow fields in supersonic inlet have been simulated using the Navier - Stokes （ N - S） equations which employ method of Computational Fluid Dynamics（CFD） with TVD scheme for spatial discretization and implicit LU -SGS for time integration. The characteristic of flow fields in supersonic inlet and the interaction of shock waves and boundary layer are attentively analyzed. The results of numerical simulation indicate the basic physical phenomenon. The method used in this paper is proved to be feasible. Moreover, the results of numerical simulation play a part in the design of supersonic inlet.
出处
《计算机仿真》
CSCD
2008年第6期75-78,共4页
Computer Simulation
关键词
进气道
激波
边界层
数值模拟
Supersonic inlet
Shock waves
Boundary layer
Numerical simulation
