Accession Number : AD0267362

Title :   WING LEADING EDGE OPTIMIZATION FOR AERODYNAMIC HEATING OF GLIDE RE-ENTRY VEHICLES

Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OHIO

Personal Author(s) : RUSSELL,RICHARD ERNEST

Report Date : AUG 1961

Pagination or Media Count : 1

Abstract : An investigation was made of means of reducing temperatures on the wing leading edge of hypersonic glide re-entry vehicles. A heat transfer analysis was made of an arbitrary shaped wing leading edge. The analysis includes convection, internal and external radiation, and conduction as mechanisms of heat transfer. The wing leading edge temperature distribution is obtained from a computer program. An investigation was conducted for a typical re-entry vehicle. The basis of results obtained was the temperature distribution on a cylindrical leading edge, obtained without conduction or internal radiation in the analysis. The variables considered were exterior shape back plate shape and orientation, and the physical properties of conductivity, emissivity and wall thickness. A reduction in peak nose temperature of about 700 F was obtained by optimization of the exterior shape, orientation of the back plate and by including conduction and radiation in the analysis. The investigation of material properties demonstrated that external emissivity is the only property of major consequence. (Author)

Descriptors :   *AERODYNAMIC HEATING, *REENTRY VEHICLES, CONVECTION, GLIDERS, HEAT TRANSFER, HYPERSONIC VEHICLES, REDUCTION, THEORY, THERMAL RADIATION, WINGS

Distribution Statement : APPROVED FOR PUBLIC RELEASE