Turbulence amplification in the shock wave/turbulent boundary layer interaction over compression ramp by the flux reconstruction method

摘要

Wall-resolved large eddy simulation on a supersonic turbulent boundary layer over a 24 degrees compression ramp is performed under the framework of high order discontinuous methods for a free-stream Mach number M-infinity = 2.9 and Reynolds number Re-infinity = 5.966 x 10(6). The turbulent flow is resolved by the high order flux reconstruction method, and the shock is captured by a high-resolution, but stable weighted essentially non-oscillation limiter. The solver used in this paper is validated by the double Mach reflection case and the Taylor-Green vortex case. The results of shock wave/turbulent boundary layer interaction at the ramp corner are validated by the numerical simulations and the experimental data in the literature. The analysis of the physics behind the turbulence amplification at around the ramp corner is presented. The shear effects and the flow deceleration/acceleration are the main reasons of the turbulence amplification.