二维超/高超声速进气道流场数值模拟  

Numerical Simulation of Two-Dimensional Super/Hypersonic Inlet Flowfields

作　　者：王军旗[1] 倪招勇[2] 李素循[2] 孙茂[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院 [2]北京空气动力研究所,北京100074

出　　处：《航空学报》2005年第2期153-157,共5页Acta Aeronautica et Astronautica Sinica

基　　金：863计划(2002AA725011)资助项目

摘　　要：对超/高超声速三级压缩进气道流场进行了数值模拟,来流马赫数为4、6,进气道内流动为层流状态,根据二维Navier Stokes方程,采用二阶精度Roe格式进行离散。按照流场特点,合理地设计网格分布及调整不同黏性范围的熵修正,防止了壁面附近过大的数值耗散,使计算结果更加合理。在进气道模型的各级压缩折转角处,获得了清晰的激波结构,在进气道内部的各种波系的相交、反射和激波诱导的边界层分离等现象都得到合理的描述。计算得到的压力分布,在各级压缩斜板上同简单波理论结果十分接近。用本文方法计算了另一个二级压缩进气道,沿上、下壁面的压力分布与试验比较符合得较好。A numerical method for the simulation of two-dimensional super/hypersonic laminar flows in inlet is presented. The inflow Maeh numbers are 4 and 6. The flowfields are simulated numerically by two-dimensional Navier-Stokes equations with two-order Roe＇s scheme. Basing on the characteristics of the flows, the grid layout is designed properly and the parameters within entropy fix are adjusted carefully, so that the results are given further accurately. The shock waves at the compression corners are sharply resolved. The reflections and intersections of various shock waves in the inner of the intake and the separation flows induced by shock wave/ boundary layer interaction are displayed reasonably. The comparisons of pressure distributions along the lip and ramp of another model computed by the present method with those by Keuk＇s simulation and experiment show good agreement.

关 键 词：进气道 超/高超声速流 激波/边界层干扰 数值模拟 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]