확률적 최적화 기법을 이용한 초음속 흡입구 형상설계

Two dimensional air intake for ramjet missile flying over Mach 4.0 is designed by using stochastic optimization method. The constraints from system requirement and the governing variables for intake compression are selected for design parameters. Theoretical supersonic flow equations and experimental equations for subsonic diffuser are used to construct the cost function which is total pressure recovery ratio. The optimization method, PSO, which can search the optimal solution through stochastic method in wide domain is used for optimization. The geometry from the result is verified by comparing with the CFD analysis, which shows good accordance in total pressure recovery ratio.