Hypersonic inviscid and viscous flow over a wedge and cone

Abstract

An analysis of hypersonic flow over a wedge and cone is developed that is based on hypersonic smalldisturbance theory in combination with laminar boundary-layer theory. The parameters that determine the flow are the ratio of specific heats ( = 1.4), the freestream Mach number, which ranges from 4 to 10, the wall half-angle, equal to 5, 10, or 15 deg, a wall to freestream temperature ratio, equal to 1 or 3, a Reynolds number (= 106), and a geometric parameter that is zero for a wedge and unity for a cone. All results are nondimensional and in a convenient form for establishing trends or for comparisons with experimental or CFD data. Results are provided for the inviscid surface values of the pressure, temperature, and Mach number; wave and viscous drag coefficients and several heat transfer coefficients; the maximum temperature and its location inside the boundary layer; and a variety of viscous and thermal boundary-layer thicknesses. The independent parameter is the freestream Mach number; the dependence on the wall to freestream temperature ratio and a Reynolds number are explicitly given.