The generation of shock waves is inevitable in supersonic cruise which results in the generation of wave drag as well as sonic boom on the ground. Some innovative concepts as supersonic biplane concept and supersonic twin-body fuselage concept have been proposed in recent to reduce the supersonic wave drag dramatically. In this study, the aerodynamic and sonic boom performance of innovative supersonic transport (SST) wing-body configurations is discussed by numerical approaches. This study is performed to obtain design knowledge for the innovative SST by using an optimization method of Kriging response surface model and genetic algorithm. The wing section shape of Busemann type biplane / twin-body model is optimized under the conditions of design Mach number of 1.7 and angle of attack of 2 degrees. The optimized results show the tradeoff relationship between lift-drag ratio and maximum overpressure of sonic boom distribution on the ground. It is confirmed that L/D is mainly affected by the thickness difference between the upper / lower wings. On the other hand, the maximum overpressure is mainly affected by the lower surface shape of the lower wing, to make the pressure wave pattern of "expansion-compression-expansion", which can attenuate the pressure waves propagating to the ground.
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