Direct numerical simulation of shock wave/boundary layer interaction controlled by steady microjet in a compression ramp  

作　　者：Ruoye XIAO Dong SUN Jian YU 

机构地区：[1]School of Aeronautic Science and Engineering,Beihang University,Beijing 100191,China [2]State Key Laboratory of Aerodynamics,Mianyang 621000,China

出　　处：《Chinese Journal of Aeronautics》2024年第10期83-102,共20页中国航空学报（英文版）

基　　金：Supported by the National Natural Science Foundation of China(Nos.11972064,92052104);the Key Laboratory of Computational Aerodynamics,AVIC Aerodynamics Research Institute,China(No.YL2022XFX0405);the Fundamental Research Funds for the Central Universities,China.

摘　　要：Shock wave/boundary layer interaction in a 24°turning angle of the compression ramp at Mach number 2.9 controlled by steady microjet is investigated using direct numerical simulation.Three different jet spacings which are termed as sparse,moderate and dense are considered,and the induced vortex system and shock structures are compared.A moderate jet spacing configuration is found to generate counter-rotating vortex pairs that transport high-momentum fluid towards the vicinity of wall and strengthen the boundary layer to resist separation,reducing the separation region.The dense jet spacing configuration creates a larger momentum deficit region,reducing the friction downstream of the corner.Analysis of pressure and pressure gradient reveals that dense jet spacing configuration reduces the intensity of separation shock.The impact of varying jet spacings on the turbulent kinetic energy transport mechanism is also investigated by decomposing the budget terms in the transport equation.Furthermore,the spectral characteristics of the separation region are studied using power spectral density and dynamic mode decomposition methods,revealing that moderate jet spacing configuration suppresses low-frequency fluctuations in the separation region.

关 键 词：Shock wave/boundary layer interaction Compression ramp Steady microjet Different jet spacings Direct numerical simulation 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]