摘要
本文给出了由后掠压缩角模型引起的激波和湍流边界层干扰的实验研究结果,着重提出了柱形干扰中的尺度特性。本实验中的马赫数为1.79,2.04和2.50,相应的雷诺数为2.42～2.47×10~7/米。模型后掠角的变化范围是0°到60°,流向压缩角的变化范围为0°到30°。实验结果表明,在本实验的马赫数范围内,干扰流动的上游影响区呈现柱形或锥形,如果考虑横流效应,柱形干扰区的上游影响尺度能和二维压缩角的上游影响尺度相关联。其相关关系仅受后掠角和来流马赫数的影响,而与压缩角大小无关。
An experimental investigation about three-dimensional shock wave and turbulent boundary layer interaction with swept compression corners has been carried out in BUAA. The swept angles range from 0° to 60° and the streamwise corner angles from 10° to 30°. Three freestream Mach numbers 1.79,2.04 and 2.50 were used with Reynolds number 2.42 - 2.47 × 107/m . The experimental results have indicated the existence of cylindrical and conical flow regimes in the interactions at present Mach number range. The boundary of cylindrical/conical regime occurs at higher as,λ value with increasing free-stream Mach number. The upstream influence length in cylindrical regime can be correlated with that of 2D compression corner. Finally the Mach number effect and crossflow effect on this correlation were also obtained from present study.
出处
《空气动力学学报》
CSCD
北大核心
1990年第3期280-285,共6页
Acta Aerodynamica Sinica
基金
国家自然科学基金
关键词
激波
边界层
后掠压缩角
干扰
柱形
shock wave boundary layer interaction, swept compres-sion corner,cylindrical interaction.
