Direct Numerical Simulation of Strong Shock Wave and Boundary Layer Interactions in a Compression Corner
GUO Tongbiao1， ZHANG Ji1，2， LI Xinliang1，2
1. State Key Laboratory of High Temperature Gas Dynamics， Institute of Mechanics， Chinese Academy of Sciences， Beijing 100190， China； 2. School of Engineering Science， University of Chinese
Academy of Sciences， Beijing 100049， China
Abstract：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.
郭同彪, 张吉, 李新亮. 压缩拐角强激波边界层干扰直接数值模拟研究[J]. 空天防御, 2024, 7(2): 29-35.
GUO Tongbiao, ZHANG Ji, LI Xinliang. Direct Numerical Simulation of Strong Shock Wave and Boundary Layer Interactions in a Compression Corner. Air & Space Defense, 2024, 7(2): 29-35.
