Investigation Of The Correction Of Boundary-layer On Inward Turning Hypersonic Inlet

The hypersonic inlet, as an important component part of the scramjet, acts a significant part in the development of the air-breathing hypersonic vehicle. The performance of it directly related to the performance of engine and vehicle. In this article, first the three dimensional"Jaws"hypersonic inward turning inlet with the outlet of roundness section is designed to use FORTRAN program software following the main method of the technology of streamline tracing, and the basic design flow field of the inlet is a three dimensional flow field with four planar shock waves which is produced by two oblique compression surfaces in the yaw and pitch plane with the free stream at 7 Mach number into an angle ( the two angle strategies are 9°-9°and 8°-7°); Then using FLUENT numerical analysis software its'flow characteristic and performance under design point /off design point and inviscid /viscous state are analyzed. On account of the existence of boundary-layer in viscous condition, the boundary-layer should to be corrected. And its'flow characteristic and performance also are analyzed.The results indicate: On design point, the flow field of the innovative inward inlet is in keeping with the design flow field, well positioned to meet the design requirement; The inlet still has high mass capture and compression capability on off design point; Compared with the other inlet, the inlet based on 8-7 inviscid flow field has higher mass capture and compression capability on off design point, so it can more satisfied the design requirement.In addition, the existence of viscous makes a difference between the flow characteristic and performance of the inlet and non-stick design theory, so the program of the two-dimensional compression boundary-layer equation to correct the boundary-layer according to the inlet boundary layer displacement thickness is used. The equation is provided by Cebeci and Bradshaw, and the solving method is finite difference method. Through the correction of boundary-layer, the various performance parameters of design state are closer to the inviscid design parameters; The off-design performance is also improved a lot.