Tomography-like flow visualization of a hypersonic inward-turning inlet  

作　　者：Yiming LI Zhufei LI Jiming YANG 

机构地区：[1]Department of Modern Mechanics,University of Science and Technology of China,Hefei 230027,China

出　　处：《Chinese Journal of Aeronautics》2021年第1期44-49,共6页中国航空学报（英文版）

基　　金：supported by the National Natural Science Foundation of China(Nos.11772325,11872356 and 11621202)。

摘　　要：The flow field in a typical inward-turning inlet was visualized using the Planar Laser Scattering(PLS)method in a shock tunnel with a nominal Mach number of 6.The opaque inlet,which is truncated at a series of sections,and the following transparent isolator,are combined to enable the optical access at different streamwise locations.The sequential PLS images provide a tomography-like flow visualization,which confirm the existence of streamwise Counter-rotating Vortex Pairs(CVPs)in both external and internal flow field of the inlet.Generation mechanisms of these CVPs are unraveled with the help of a numerical simulation,among which the cowl notch plays an important role in the generation of surface trailing CVPs along the centerline of the cowl.Moreover,the cowl shock sweeps the internal boundary layer towards the body side,which ultimately accumulates low-momentum flow on the body side in forms of a large CVP propagating downstream through the isolator.The CVPs formed in the shape-transition are responsible for the nonuniform flow field of the inward-turning inlet.This study indicates that the V-shaped cowl notch affects the downstream flow significantly and,therefore,should be examined thoroughly in practical applications.

关 键 词：Counter-rotating Vortex Pair(CVP) Flow visualization Inward-turning inlet Planar Laser Scattering(PLS)method Shock wave 

分 类 号：V211.48[航空宇航科学与技术—航空宇航推进理论与工程]