Shells With Binary Mixed Compression Supersonic Inlet Design And Test Research

Due to the good performance and potential appliance dominance of the solid rocket ramjet,the attention of many countries focuses on the study of the solid rocket ramjet. Consequently the study of supersonic inlet is significant in theory and engineering application.This thesis introduces the development of the solid rocket ramjet technology domestically and abroad. Characteristics of supersonic inlet are analyzed in this paper. The design methods of two-dimensional and three-dimensional mixed compression supersonic inlet and isolater are studied. The two-dimensional mixed compression supersonic inlet with wedge lip is designed by using the method of equal shock wave intensity. The software was employed to simulate the flow field of the design and off-design conditions. The optimal scheme was determined by adjusting the model size of two-dimensional inlet and the distribution of inlet. On the basic of theory analysis, a 1/3 scale model of a 2-D mixed-compression supersonic intake was tested. the two-dimensional mixed compression supersonic inlet has been studied experimentally and numerically.Through many schemes design and filter of 2-D mixed-compression supersonic intake, confirm the design scheme of experimental investation. The experimental results show that according as this design method, to a certainty range of mach number, attack angle and sideslip angle, intake has favorable capability. In the process of study, it is a supernal efficiency and reasonable and feasible technical route to designed by one-dimensional wave series theory and confirmed the model size of inlet by two-dimensional numerical simulation and confirmed the distribution of inlet by the three-dimensinal numerical simulation and tested by wind tunnel test of reduced scale model.