关键词: 湍流, 转捩, 超声速边界层, 激波/湍流边界层干扰, 大涡模拟

Abstract: With an aim to realize hypersonic inlet turbulent separation control, a study is made of the inlet shock wave/turbulent boundary layer interaction (SWTBLI). As a sample, a plane flat shock wave reflection flow is simulated by large eddy simulation (LES). Shock wave effect mechanism in Mach number 3.0 conditions is analyzed. In the process of unsteady LES, disturbances that are obtained by direct numerical simulation (DNS) are imposed on the initial laminar boundary layer circularly to achieve full turbulent boundary quickly. When full turbulent boundary is realized, an oblique shock wave is imposed on it to form the SWTBLI. The numerical results indicate that LES can simulate planar SWTBLI well. The separation extent of the shock wave interaction zone is consistent with the experiment data. Owing to the effect of shock wave compression, the thickness and strength of the boundary layer are reduced near the reflecting shock wave.

Key words: turbulence, transition, supersonic boundary layer, shock wave/turbulent boundary layer interaction, large eddy simulation