Inverse Design and Experiment of Hypersonic Curved Shock Wave Compression Inlet

Abstract

On the basis of the basic concepts of the curved compression and the inverse design of the curved shock wave in the previous chapters, we will introduce some practical design methods for this new design concept in this chapter, including the inverse design of the curved compression two dimensional inlet with three sections of pressure rising on the external compression section, the design of the curved compression two dimensional inlet with the internal and external compression surface full channel with controllable pressure rising, the inverse design of the curved compression axisymmetric inlet with controllable pressure rising, the inverse design of the side wall curved compression inlet with controllable Mach number distribution and the inverse design of the curved compression inward turning inlet. After the theoretical design is completed, the boundary layer of the molded surface of the inlet compression surface is corrected. We must emphasize that the four inlet pneumatic design examples introduced in this chapter are only to illustrate how to specifically design a whole process of the inlet starting from the pneumatic parameter distribution without deliberately pursuing the high performance of a certain aspect. There is no doubt that the high comprehensive performance of the curved compression inlet, the large potential of performance improvement, the flexible design means can provide a wider design platform for the designer of the hypersonic compression system to achieve some special needs.