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

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.