1955•NASA STI Repository (National Aeronautics and Space Administration)Requires access
Lift, drag, and longitudinal stability at Mach numbers from 1.4 to 2.3 of a rocket-powered model having a 52.5 degree sweptback wing of aspect ratio 3 and inline tail surfaces
Warren Gillespie
Open publisher page 0 citations
Abstract
Report presenting an investigation of a configuration with a body of fineness ratio 16.9, a 52.5 degree sweptback wing of aspect ratio 3, taper ratio 0.2, and NACA 65A004 airfoil section, and an incline tail which was aeropulsed continuously in pitching during free flight with and without a sustainer rocket motor operating. The Mach number range covered was from 1.4 to 2.3. Results regarding drag, total normal force and pitching moment, wing normal-force-curve slope, flow conditions at the horizontal tail, and cross coupling are provided.