首页|压缩拐角强激波边界层干扰直接数值模拟研究

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

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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.

shock wave/turbulent boundary layer interactiondirect numerical simulationflow structureflow separationturbulent kinetic energy

郭同彪、张吉、李新亮

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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

中国科学院大学 工程科学学院,北京 100049

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

国家重点研发计划中国博士后科学基金中国航天科技集团有限公司上海航天科技创新基金

2019YFA04053002022M723232SAST2021-001

2024

空天防御
上海机电工程研究所和上海交通大学出版社有限公司

空天防御

ISSN：2096-4641
年,卷(期)：2024.7(2)
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