Integrative Hypersonic Waverider Design Based On Osculating Cones Method

An airframe/propulsion integrative hypersonic waverider design method based on osculating cones is developed in this dissertation. The design method is proved to be convenient and effective for integrative design of hypersonic vehicle.Both the wave drag and the friction drag increase as the Mach number becomes higher for hypersonic flow ; moreover , a technique difficult will appear which is called L/D barrier. The waverider aerodynamic configuration may be a way to overcome this barrier. A osculating cones hypersonic waverider is generated based on the wedge-derived and cone-derived flow field at the conditions of Ma∞=5.0～10.0 , and shock angle differed from 9°to 13°. The osculating cones method can be seen as a generic waverider design method which has the advantage both of wedge-derived waverider and cone-derived waverider, such as symmetrical flow, large L/D, good volumetric efficiency and other aerodynamics performance.The purpose of airframe/propulsion integrative design is to compress the hypersonic flow with vehicle forebody, to capture enough air flow to satisfy the combustor, and to provide symmetrical flow to the inlet. The shockwaves from the inlet ramps is cancelled at the cowl lip of the scramjet engine. The shape of the inlet ramps is determined by both the shape of vehicle forebody and scramjet engine. The air coming from the wedge-derived forebody flows though three inlet ramp shockwaves to the scramjet engine, and then flow out though divergence section and combustor. The aftbody is defined purely geometrically.The configuration has been numerically verified by solving the N-S equations. It shows that the aim of integrative design is attained and high lift-to-drag ratio is achieved.