Results are presented of a study on the aerodynamics of a new type of waverider derived from supersonic axisymmetric ows inside constricting ducts, speci cally conical trumpet ducts. In such a duct, an initial shock wave arises from its leading edge, and the compression ow downstream of this shock has streamlines converging toward the ow axis. This ow is chosen as a basic ow for the waverider design. The simplest convergent-owderived waveriders are constructed with a lifting surface with a transverse-concave arc-shaped contour. They are compared with known types of waveriders constructed based on uniform ows behind plane oblique shock waves or divergent ows behind axisymmetric conical shock waves. The characteristics of convergent waveriders as lifting con gurations are analyzed with the lift and drag coef cients, the lift-to-drag ratio, and the integral heat uxes through the waverider surfaces determined. The possibilities of using these new waveriders as forebodies for hypersonic vehicles powered by airbreathing engines are also estimated. The ow eld characteristics near the lower lifting surface of the waverider as a precompression surface arranged upstream of the inlet are considered in this connection.
Nomenclature
C D= drag coef cient, D/ (q 1 S pl ) C L = lift coef cient, L / (q 1 S pl ) L / D = lift-to-drag ratio L w = waverider length, m L w = relative length of a waverider, L w / R 0 M = ow Mach number p = relative static pressure, p/ p 1 q 1 = freestream dynamic pressure, Pā R e = relative radius of transverse curvature of a lifting surface in the end cross section of a waverider, R e / R 0 R s = relative radius of a trumpet-shaped shock wave, R s / R 0 R 0 = radius of a constricting duct in the initial cross section, m S pl = reference planform area of a waverider, m 2 x,r = relative longitudinal and radial coordinates, x / R 0 and r / R 0 , respectivelȳ x a = relative longitudinal coordinate of the waverider aerodynamic center, x a / L w x e = relative longitudinal coordinate of the waverider end cross section, x e / R 0 d c = cone angle, deg d d = angle of inclination of a conical duct wall to the duct axis, deg d w = wedge angle, deg h = angle of inclination of a ow velocity vector to the duct axis, deg s = volumetric factor, 3 p (X 2 )/ S pl } = half-angle of the arc contour sector, deg X = waverider volume, m 3 Subscripts s = shock wave 1 = freestream values