Supersonic laminar boundary layers on cones

Abstract

The boundary layer flow over a cone inclined at a small angle to a supersonic stream, and over a type of caret (Maikapar, Nonweiler) surface, as generalised by Townend, is calculated by an implicit finite difference method. Prandtl number is arbitrary but viscosity must follow the Chapman-Rubesin law. Any (conical) distribution of wall temperature or heat flux can be covered; the effects of suction or blowing can only be included if the normal velocity along a ray varies inversely as distance from the apex. Some sample calculations are made. The method begins to break down as separation is approached, but it is not difficult to find the separation line by extrapolation.