Accession Number : AD0431275


Title :   DEVELOPMENT OF AERO-THERMODYNAMIC PROCEDURES FOR DESIGNING HIGH SPEED VEHICLE LEADING EDGES,


Corporate Author : NORTH AMERICAN AVIATION INC COLUMBUS OHIO


Personal Author(s) : McCullough,J K


Report Date : Jan 1943


Pagination or Media Count : 309


Abstract : Aerodynamic and thermodynamic procedures were developed for analyzing and designing heat-sustaining leading edges and forebodies of highspeed aircraft and missiles. A series of design charts is presented for symmetrical, blunted wedge, and conical leading edges that enable the user to predict steady state surface temperature distributions of radiation-cooled nose sections while considering aerodynamic drag. The methods and design charts apply to flight speeds between Mach 2 and Mach 24, and altitudes between sea level and 220,000 feet. In adition, a sample structural analysis was conducted for two different leading edge shapes of a swept wing being maintained at a flight condition of Mach 3.5 at 80,000 feet altitude. The results apply to aircraft, missiles and glide reentry vehicles operating under quasi-steady flight conditions. (Author)


Descriptors :   *DELTA WINGS , LEADING EDGES , DRAG , HYPERSONIC CHARACTERISTICS , AIRCRAFT , GUIDED MISSILES , SHOCK WAVES , HEAT TRANSFER , CONICAL BODIES , WEDGES , BLUNT BODIES , TEMPERATURE , DISTRIBUTION , SWEPTBACK WINGS


Distribution Statement : APPROVED FOR PUBLIC RELEASE