高超声速楔面边界层流动稳定性分析

推进技术 ›› 2012, Vol. 33 ›› Issue (5): 671-675.

高超声速楔面边界层流动稳定性分析

张红军,袁湘江,沈清

中国航天空气动力技术研究院,北京 100074;中国航天空气动力技术研究院,北京 100074;中国航天空气动力技术研究院,北京 100074

发布日期:2021-08-15
作者简介:张红军(1976—),男,硕士,高级工程师,研究领域为流体力学计算及试验。E-mail: zhhj76529@sina.com
基金资助:
国家自然科学基金(90816026；10872018)。

Analysis on Boundary Layer Flow Stability of Hypersonic Wedge

China Academy of Aerospace Aerodynamics,Beijing 100074,China;China Academy of Aerospace Aerodynamics,Beijing 100074,China;China Academy of Aerospace Aerodynamics,Beijing 100074,China

Published:2021-08-15

摘要/Abstract

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。

关键词: 边界层;线性稳定性分析;钝化效应

Abstract: 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=0.5mm 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 characteristic.

Key words: Boundary layer；Linear steady analysis；Bluntness effect

张红军,袁湘江,沈清. 高超声速楔面边界层流动稳定性分析[J]. 推进技术, 2012, 33(5): 671-675.