Efficient Global Optimization of a Novel Diverterless Supersonic Intake Design Method

A diverterless supersonic intake (DSI) design method using a novel blending method is proposed, offering key design parameters that define the DSI bump and cowl geometry. The new method provides a seamless connection between the bump and the fuselage geometry and is applicable to the curved body fuselage. An efficient global optimization method is used to obtain the optimal design while minimizing the time-consuming numerical analysis, which was inaccessible with conventional techniques. The performance evaluation set is built by tuning the bump surface geometry and the cowl sweep angle by varying design parameters, and an expected improvement in-fill method is used to construct the accurate Kriging surrogate model. The optimal design obtained from the surrogate model is thoroughly analyzed and compared with the base design, which showed an impressive 38.3% enhancement in the performance index, the total momentum. The flow field analysis showed that the improved compression efficiency and boundary layer removal with minimal flow loss led to enhanced performance.