An Inviscid Computational Method for Tactical Missile Configurations.

摘要

A finite difference method suitable for design calculations of finned bodies is described. Efficient numerical calculations are achieved using a thin fin approximation which 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 which 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. Calculated forces and moments on body-wing-tail configuration with subsonic leading edges are compared to experiment also. Body alone configurations are studied using a Kutta condition to generate a lee-side vortex.