Accession Number:

AD0431275

Title:

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

Descriptive Note:

Corporate Author:

NORTH AMERICAN AVIATION INC COLUMBUS OHIO

Personal Author(s):

Report Date:

1943-01-01

Pagination or Media Count:

309.0

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

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE