高超声速湍流分离激波运动特性  

Separation Shock Motion Features in a Hypersonic Turbulent Flow

作　　者：王世芬[1] 任志远[1] 

机构地区：[1]中国科学院力学研究所

出　　处：《空气动力学学报》1998年第3期343-347,共5页Acta Aerodynamica Sinica

基　　金：国家自然科学基金

摘　　要：给出半圆柱前缘舵诱导的高超声速湍流分离激波运动特性。实验气流Ｍ数为７．８，单位长度Ｒｅ数为３．５×１０７／ｍ。结果表明，随着Ｍ数的增加，分离激波两边压力比的平均值加大，但对其用前缘直径无量纲的激波运动区长度和用自由流速度无量纲的激波向上（下）游运动速度的平均值影响不大。This paper presents the separation shock motion features induced by a hemicylindrically blunted fin in a hypersonic turbulent flow.The nominal test conditions were freesteam Mach number of 7.8 and unit Reynolds number of 3.5×10 7/m.The results show that the mean pressure ratio across the separation shock increases with Math number.However,Mach number variation has little effect on the streamwise length scale of the separation shock motion normalized by leading edge diameter and mean shock velocities normalized by the freestream velocity in both upstream and downstream directions.

关 键 词：高超声速 分离流 激波运动 钝缘舵 舵 湍流分离 

分 类 号：V211.19[航空宇航科学与技术—航空宇航推进理论与工程] V211.43