| Hypersonic inlet is the compression component of the hypersonic scramjet, the performance of the inlet has direct effect on the overall efficiency of the scramjet, so it is very important to pay more attention to the study of the inlet, and in this thesis a three dimensional sidewall compression inlet has been studied experimentally and numerically.A 3d LU-SGS computational code is developed to solve the hypersonic flows, which is modeled by the compressible Reynold averaged three-dimension Navier-Stokes equations and with a use of a finite volume formulation, the convective parts are discretized with the Harten TVD scheme, turbulent effects are modeled utilizing Menter SST tow equation turbulence model. This code is validated by compare the computation results of the problem of three dimension crossing-shock wave/turbulent boundary layer interaction with either experiments or computations of other authors. And the wind-tunnel testing of a three dimensional, sidewall compression hypersonic inlet SC01 has been conducted at Mach 5.2, the experimental results are analyzed to identify the effects of the performance of the inlet by changing cowl position, and computations of several simplified model of different type of three dimensional sidewall compression scramjet inlet are compared and synthesized to solve the flow in the inlet and offer evidence for the further design of the three dimensional sidewall compression scramjet inlet.
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