Design and Optimization of Scramjet Overall Scheme

According to the specific task requirements, the scramjet basic general scheme and optimization scheme are designed. Based on the oblique shock theory, the inlet model is constructed according to the design principle of maximum total pressure recovery coefficient. The isolation section model is constructed and the parameters of the isolation section are estimated by the pressure rise ratio. Based on the quasi-one-dimensional flow theory, a quasi-one-dimensional analysis model including combustor and exhaust nozzle is constructed, considering the injection point setting, expansion angle setting, wall friction and combustion efficiency. The basic design scheme and corresponding engine performance are obtained by sorting out the analysis results. The optimization model is constructed by genetic algorithm, and the optimization scheme is retrieved with the maximum thrust as the target. The performance of the optimized scheme is compared with that of the basic scheme, and the design advantages of the optimized scheme are analyzed.