高超音速进气道粘性流场的分块计算  

SIMULATION TO VISCOUS FLOW OF A SUPERSONIC INLET BY MULTIBLOCK METHOD

作　　者：刘晶昌[1] 徐建中[1] 

机构地区：[1]中国科学院工程热物理研究所,北京100080

出　　处：《工程热物理学报》1997年第6期695-699,共5页Journal of Engineering Thermophysics

基　　金：国家863计划资助

摘　　要：本文采用一种隐式迎风型TVD格式求解二维Navier—Stokes方程，使用分块技术数值模拟了某超音速进气道在飞行马赫数2．291和2.557两种状态下的流动，给出了该进气道的内外流场结构、捕获面积比、表面压力分布、总压恢复系数等等。Flow in a supersonic inlet under two Mach numbers 2.291 and 2.557 was simulated by solving two dimensional Navier-Stokes equations. The equations were discretized by upwind TVD scheme, and the multi-block method was applied in order to obtain whole flowfield at the given exit pressure. The shock structures, captured area ratios, surface pressure distributions and total pressure recovery coefficients of this supersonic inlet were given in this paper.

关 键 词：高速进气道 N-S方程 粘性流场 计算 

分 类 号：TK12[动力工程及工程热物理—工程热物理] TK14[动力工程及工程热物理—热能工程]