A diverterless supersonic intake (DSI) integrated into a cylindrical fuselage is designed and evaluated. The method of designing the intake is newly defined and presented in this study. It uses a streamline-traced compression surface and two blending functions to generate a curved-body integrated 3-D bump surface. Each blending function uses an exponential function whose exponent is defined as a design parameter, allowing the independent modification of the bump shape. A numerical analysis of the designed intake found that a spanwise pressure gradient generated by the bump pushes away the thick boundary layer developed at the fuselage wall. This improves the quality of the flow captured at the intake. Also, the ability of ramjet mode operation of the intake is assessed by inducing a critical operating condition to the intake. This causes a terminal shockwave that decelerates the oncoming supersonic flow to a subsonic flow. The stagnation pressure recovery of 0.37 at the design Mach number 2.8 is achieved when the static back pressure ratio of the intake is 7.37. The analysis showed that a DSI designed using the methodology developed in the study can operate as a ramjet intake, with the boundary layer control effect provided by the bump.