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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.
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Received: 19 April 2023
Published: 10 May 2024
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2024, Vol. 7 
