Convergent-flow-derived waveriders

Results are presented of a study on the aerodynamics of a new type of waver ider derived from supersonic axisymmetric hows inside constricting ducts, s pecifically conical trumpet ducts. In such a duct, an initial shock wave ar ises from its leading edge, and the compression flow downstream of this sho ck has streamlines converging toward the flow axis. This how is chosen as a basic flow for the waverider design. The simplest convergent-flow-derived waveriders are constructed with a lifting surface with a transverse-concave are-shaped contour. They are compared with known types of waveriders const ructed based on uniform flows behind plane oblique shock waves or divergent flows behind axisymmetric conical shock waves. The characteristics of conv ergent waveriders as lifting configurations are analyzed with the lift and drag coefficients, the lift-to-drag ratio, and the integral heat fluxes thr ough the waverider surfaces determined. The possibilities of using these ne w waveriders as forebodies for hypersonic vehicles powered by airbreathing engines are also estimated. The flowfield characteristics near the lower li fting surface of the waverider as a precompression surface arranged upstrea m of the inlet are considered in this connection.