Numerical Simulation Of Hypersonic Inlet Flows

Hypersonic inlet is one of the most important components of the hypersonic scramjet, and its performance has direct effect on the overall efficiency of the scramjet, so it has been paid high attention and a lot of experimental and numerical researches are developed on it. In this dissertation, multigrid method is implemented in numerical computation to simulate the inner flowfield of hypersonic inlet, and the results are accordant with correlative literatures. The primary work is as follows:1. Highly-efficiency multigrid method is implemented in numerical computation of 2D and 3D Navier-Stokes equations. The flow solver is a cell-centered, finite volume scheme applied to compressible Reynolds averaged three-dimensional Navier-Stokes equations. The inviscid fluxes are computed using Harten-TVD scheme and the two-equation turbulence model of Menter SST is used for simulation of turbulent effects. The temporal discretization is done using implicit LU-SGS method.2. Different V/W type cycles are compared on computation results and efficiency in 2D problem, and a most effective multigrid formulation is presented.3. Using this effective formulation in 3D problem, a multigrid formulation involved on three-dimensional Navier-Stokes equations is developed.4. The effect of cycle types, iteration numbers on each layer and CFL number on computation efficiency is discussed.5. The problems of supersonic flat turbulent boundary layer and three dimension crossing-shock wave/turbulent boundary layer interaction are simulated, and the current multigrid method is proved to be efficient and robust.