作者: Ge-Cheng Zha , Donald Smith , Mark Schwabacher , Khaled Rasheed , Andrew Gelsey
DOI: 10.2514/2.2241
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摘要: A multilevel design strategy for supersonic missile inlet is developed. The combines an efe cient simple physical model analysis tool and a sophisticated computational e uid dynamics (CFD) Navier ‐ Stokes tool. incorporated into the optimization loop, CFD used to verify, select, lter nal design. genetic algorithms multistart gradient line search optimizers are nonsmooth space. geometry that starts at Mach 2.6 cruises 4 was designed. Signie cant improvement of total pressure recovery has been obtained. Detailed owe eld also presented.