激波与湍流边界层干扰流动的马赫数效应  

Mach number effect in shock-wave/turbulent-boundary-layer interaction flow

作　　者：吴正园 高振勋[1] 陈新民 蒋崇文[1] 李椿萱[1] 葛航 WU Zhengyuan;GAO Zhenxun;CHEN Xinmin;JIANG Chongwen;LEE Chunhian;GE Hang(School of Aeronautic Science and Engineering,Beihang University,Beijing 100191,China;The Institute of Advanced Manufacturing Technology,Ningbo Institute of Materials Technology&Engineering,Chinese Academy of Sciences,Ningbo 315336,China)

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191 [2]中国科学院宁波材料技术与工程研究所先进制造技术研究所,宁波315336

出　　处：《北京航空航天大学学报》2024年第11期3484-3494,共11页Journal of Beijing University of Aeronautics and Astronautics

基　　金：国家自然科学基金(11872094);国家自然科学基金创新研究群体项目(11721202)。

摘　　要：激波与湍流边界层相互干扰(SWTBLI)现象可诱导形成复杂的流场结构和气动力热分布特性,其干扰机制和影响机理至今仍未被充分掌握。为分析超/高超声速SWTBLI流动的机理,开展了来流马赫数为3、5、11条件下压缩拐角流动的直接数值模拟(DNS)研究。结果显示,SWTBLI使干扰区内的速度、压强等物理量的脉动显著增强,且增强幅值随来流马赫数升高而增大;同时,上游边界层中的温度、压强等物理量的脉动也随来流马赫数的增大而增强。在SWTBLI作用下,流动的可压缩效应明显增强,干扰区内压力膨胀项和膨胀耗散项不再可忽略。在高超声速条件下,上游边界层中的压力膨胀项和膨胀耗散项也比较重要。此外,SWTBLI诱导的壁面压强平均值和脉动均方根值的分布存在共性。在所有来流马赫数下,干扰区内的壁面压强脉动相比上游边界层均显著增强,并形成明显的峰值。流动发生显著分离时,将分别形成位于平均分离点和再附点附近的壁面压强脉动峰值。The shock-wave/turbulent-boundary-layer interaction(SWTBLI)phenomenon will result in complex flow structures.Direct numerical Simulation(DNS)studies of compressible corner flow under freestream mach number 3,5,11 conditions have been carried out to further explore supersonic/hypersonic SWTBLI flow mechanisms.It is found that SWTBLI causes a significant increase of turbulence fluctuation in the interaction zone,and such influence is further enhanced with the increase of freestream Mach number.Higher Mach numbers also make variations in pressure and temperature in the upstream turbulent boundary layer more noticeable.In addition,the compressible effect is also significantly enhanced by SWTBLI.Terms associated with compressible effects,including the pressure dilatation and dissipation terms,are no longer insignificant in the interaction zone and the upstream boundary layer(in the case of hypersonic travel).Furthermore,commonalities of SWTBLI-induced mean and RMS wall pressure distribution are observed.Both mean and RMS wall pressure increase rapidly through the interaction zone until reaching their peak values.Distribution of RMS wall pressure along streamwise direction shows two peak value points when a large separation zone forms,which are closely related to the mean separation point and mean reattachment point,respectively.

关 键 词：激波与湍流边界层相互干扰 高超声速流动 可压缩湍流 直接数值模拟 分离流 

分 类 号：V221.3[航空宇航科学与技术—飞行器设计] O355[理学—流体力学]