Abstract: Based on the integrated design demand of hypersonic cruise missiles, a forebody/inlet benchmark configuration was designed by the constant shock intensity method. Performances of the benchmark configuration were analyzed by means of numerical simulation. The performance response surface model was established using the Design of Experiments (DOE) and CFD results. The forebody/inlet was optimized by multi-objective particle swarm optimization (MOPSO) algorithm under the performance indices of total pressure recovery coefficient and mass capture coefficient. Performances of the optimized forebody/inlet were analyzed using CFD methods. The results show that the forebody/inlet design method is right and effective, and the benchmark configuration meets the design requirements. The forebody/inlet performances can be improved by the multi-objective optimization method. The research results provide a reference for integrated design of scramjets to be used in hypersonic cruise missiles.