Abstract: This paper develops an integrated design methodology for minimal wave drag cone-derived waveriders and three-dimensional inward turning inlets. To verify its feasibility, flow fields and compression characteristics of a novel integrated forebody inlet designed by this method are evaluated at typical flying conditions. Firstly, the design method for minimal wave drag cone-derived waveriders is introduced and verified. Then the flow fields around the inward turning cone and the integrated design method of a minimal drag cone-derived waverider with a three-dimensional inward turning inlet is demonstrated. The flow-field structures and parameters of the integrated waverider inlet at design conditions are examined in detail. The results agree well with the design expectations. Finally, the performance of the inlet of the integrated waverider at off design conditions are investigated by Computational Fluid Dynamic. The results show that the novel integrated waverider forebody inlet has desirable flow compression performance. This novel integration design method for minimal wave drag conic waveriders with there-dimensional inward turning inlet provides an alternative choice for the configuration integration of airbreathing hypersonic vehicles.