Experimental Research And Numerical Simulation Of Hypersonic Inlet

In this dissertation,both experimental and numerical methods are involved to research on the hypersonic inlet.A hypersonic wind tunnel test is performed to investigate the starting characteristics of 2D and 3D geometric inlet.Start/unstart flow field is studied by wall static pressure messurement,schlieren and wall surface oil flow pattern.The results show that the shocks and expansive waves are clearly in start inlet flow field ,while there is a large scale separation region in the forebody boundary layer of unstart inlet flow field.The flow field of 3D inlet is very complex.It presents distinct 3D characteristics.The results indicate that the starting characteristics of hypersonic inlet is greatly influenced by inner contractive ratio,the first wedge angle and the blunted wedge of the cowl.Proper choice of geometric parameters is in favor of inlet starting characteristics.Othermore,viscous flows in hypersonic inlet are simulated through solving the 2D Navier-Stokes equations on hybrid grids,and the results are accordant with experimental data.It is proved that the computational program of this paper is feasible to simulate the hypersonic inlet flow.