Abstract: A new Osculating Curved Cone method is developed for hypersonic vehicle degign, in which the method of streamlines tracing axisymmetric flow fields of multistage shockwaves or isentropic compressing waves is used to create the waverider lower surface and inlet lip inner surface. The shape of the vehicle upper surface is governed by the inward deviation from the FCT as a function of axial location, the determination of the primitive flow variables on the upper surface is accomplished through the application of a first order scheme utilizing the axisymmetric method of characteristics, so as to fullfill an accurate yet rapid computational analysis. 2D and 3D MOC tools that can quickly design and analyze nozzle geometries are developed and the performance of SCRAMJET engine is evaluated by a 1D method. A model vehicle about 3 meters long at ondesign operation point Mach 6 is presented, and the results of numerical simulations and wind tunnel experiments show that rapid analysis has a moderate accuracy. The SCRAMJET engine works well and the vehicle obtains net positive thrust at design condition.