Supersonic Inviscid Flowfield Computations of Missile Type Bodies

Abstract

A finite-differe nce method suitable for design calculations of finned bodies is described. Efficient numerical calculations are achieved using a thin fin approximation that neglects fin thickness but retains a correct description of the fin surface slope. The resulting algorithm is suitable for treating relatively thin, straight fins with sharp edges. Methods for treating the fin leading and trailing edges are described that are dependent on the Mach number of the flow normal to the edge. The computed surface pressures are compared to experimental measurements taken on cruciform configurations with supersonic leading and trailing edges and to a swept wing body with detached leading-edge shocks. A semiempirical procedure is developed to treat the leading edges in the latter case. Measured and calculated pressures are in reasonable agreement in both the tested configurations.