Abstract: The diverterless inlet and forebody of a fighter are constructed by using the Three Dimensional Reversion Technique of Photos and the external and internal flowfields of the inlet and forebody are calculated. The Mach contours inside and outside the inlet and the pressure distribution on the bump surface are presented. Mechanism of diversion of boundary layer on diverterless supersonic inlet (DSI) is also analyzed. It can be seen from the results that there is an initial compression angle at the front point of the bump and an isoentropic compression surface after the shock. The investigation shows that the diverterless supersonic inlet or bump inlet creates a high pressure area on the bump compression surface which pushes the air in boundary layer away from the inlet.

Key words: divertreless supersonic inlet (DSI), bump inlet, integrated design, computational fluid dynamics (CFD)