高超声速楔面边界层流动稳定性分析  

Analysis on Boundary Layer Flow Stability of Hypersonic Wedge

作　　者：张红军[1] 袁湘江[1] 沈清[1] 

机构地区：[1]中国航天空气动力技术研究院,北京100074

出　　处：《推进技术》2012年第5期671-675,共5页Journal of Propulsion Technology

基　　金：国家自然科学基金(90816026;10872018)

摘　　要：为分析前缘钝化对高超声速二元进气道压缩面边界层转捩的影响,针对抽象出的楔面外形,在风洞来流条件下,应用线性稳定性理论(Linear Steady Theory)分析了前缘钝化半径R=0及R=0.5mm的楔面边界层流动稳定性,得到各自前缘构形的边界层失稳位置及最不稳定波的波数和增长率。研究发现,前缘钝化半径R=0.5mm的楔面边界层失稳位置远远大于前缘钝化半径R=0的楔面边界层失稳位置,表明前缘钝化对楔面边界层失稳特性具有显著影响。To analyze the effect of leading edge bluntness on two dimensional hypersonic inlet boundary layer transition for the abstract wedge configurations, the linear stability analysis on boundary layer of wedges ,with leading edge radius R = 0 and R = 0.5mm,respectively,was carried out at the condition of wind tunnel test. The boundary layer instability station, the wave number and increasing rate of the most unstable wave were obtained with R = 0 and R = 0. 5mm respectively. It has been found that the instability station of wedges with leading edge radius R = O. 5mm is far greater than that with leading edge radius R = 0. This shows that the bluntness effect of leading edge has an observable impact on wedge boundary layer unsteady characteris- tic.

关 键 词：边界层 线性稳定性分析 钝化效应 

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]