关键词: 进气道, 超／高超声速流, 激波／边界层干扰, 数值模拟

Abstract: A numerical method for the simulation of two-dimensional super/hypersonic laminar flows in inlet is presented. The inflow Mach numbers are 4 and 6. The flowfields are simulated numerically by two-dimensional Navier-Stokes equations with two-order Roe’s scheme. Basing on the characteristics of the flows, the grid layout is designed properly and the parameters within entropy fix are adjusted carefully, so that the results are given further accurately. The shock waves at the compression corners are sharply resolved. The reflections and intersections of various shock waves in the inner of the intake and the separation flows induced by shock wave/boundary layer interaction are displayed reasonably. The comparisons of pressure distributions along the lip and ramp of another model computed by the present method with those by Keuk’s simulation and experiment show good agreement.

Key words: inlet, super/hypersonic flow, shock wave/boundary layer interaction, numerical simulation