压缩拐角强激波边界层干扰直接数值模拟研究  

Direct Numerical Simulation of Strong Shock Wave and Boundary Layer Interactions in a Compression Corner

作　　者：郭同彪 张吉 李新亮[1,2] GUO Tongbiao;ZHANG Ji;LI Xiniang(State Key Laboratory of High Temperature Gas Dynamics,Institute of Mechanics,Chinese Academy of Sciences,Beijing 100190,China;School of Engineering Science,University of Chinese Academy of Sciences,Beijing 100049,China)

机构地区：[1]中国科学院力学研究所高温气体动力学国家重点实验室,北京100190 [2]中国科学院大学工程科学学院,北京100049

出　　处：《空天防御》2024年第2期29-35,共7页Air & Space Defense

基　　金：国家重点研发计划(2019YFA0405300);中国博士后科学基金(2022M723232);中国航天科技集团有限公司上海航天科技创新基金(SAST2021-001)。

摘　　要：激波/湍流边界层干扰是高超声速飞行中常见的流动现象,平板-压缩拐角存在于飞行器进气道、翼舵等,是研究激波/湍流边界层干扰的标准构型。采用直接数值模拟方法研究了马赫数6.0、40°压缩拐角的高超声速强激波/湍流边界层干扰问题。在上游湍流边界层内,近壁流动以高低速条带结构为主;当流动进入干扰区后,流向条带消失,同时形成具有三维特征的流动结构。在强激波作用下,分离长度超过10个边界层厚度。流动再附后,壁面摩阻、压力及其脉动峰值分别达到上游湍流边界层的8.9、36和124倍。干扰区内湍动能强度显著增加,其峰值是边界层峰值的6.4倍。研究发现激波运动、分离剪切层是湍动能强度增加的主要原因。Shock wave/turbulent boundary layer interaction(SWTBLI)is a prevalent flow phenomenon in hypersonic flights.A flat plate with a compression ramp at the inlet of the engine,control surfaces and so on,has become a typical standard model for studying SWTBLI.In this paper,a direct numerical simulation was conducted to study the hypersonic strong SWTBLI caused by a 40°compression ramp at Mach number 6.0.In the upstream turbulent boundary layer,the near-wall vortical structures performed as streamwise vortices.Once entering the interaction region,the streamwise vortices disappeared,and instead,the three-dimensional flow structures were produced.Under the strong shock wave,the flow separation length exceeds ten times that of the boundary layer thickness.In the downstream of the flow reattachment where the peak of the wall skin friction,the pressure along with its fluctuation was respectively 8.9,36,and 124 times those in the upstream boundary layer.The intensity of the turbulent kinetic energy in the interaction region was significantly increased by 6.4 times that in the boundary layer.It's concluded that the turbulent kinetic energy results mainly from the shock unsteadiness and the separated shear layer.

关 键 词：激波/湍流边界层干扰 直接数值模拟 流动结构 流动分离 湍动能 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程] O241.3[理学—计算数学]