A multilevel design strategy for supersonic missile inlet design is developed. The multilevel design strategy combines an ef cient simple physical model analysis tool and a sophisticated computational uid dynamics (CFD) Navier -Stokes analysis tool. The ef cient simple analysis tool is incorporated into the optimization loop, and the sophisticated CFD analysis tool is used to verify, select, and lter the nal design. The genetic algorithms and multistart gradient line search optimizers are used to search the nonsmooth design space. A geometry model for the supersonic missile inlet is developed. A supersonic missile inlet that starts at Mach 2.6 and cruises at Mach 4 was designed. Signi cant improvement of the inlet total pressure recovery has been obtained. Detailed ow eld analysis is also presented.
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