NACA Research Memorandums

Abstract

Report of an investigation of the overall performance characteristics of a complete missile configuration in the 8- by 6-foot supersonic wind tunnel at several Mach numbers, angles of attack, canard-control-surface deflections, and a designated Reynolds number based on wing mean aerodynamic chord. The investigation showed that at a Mach number of 2.0, the addition of engines to a no-engine configuration increased drag and moved the aerodynamic center rearward but produced little additional lift. Results regarding force and moment evaluation and engine-internal-flow evaluation are provided