Accession Number : AD0256078

Title :   MEASUREMENTS OF AERODYNAMIC HEAT TRANSFER ON A 15 DEG CONE-CYLINDER-FLARE CONFIGURATION IN FREE FLIGHT AT MACH NUMBERS UP TO 4.7

Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON D C

Personal Author(s) : RUMSEY,CHARLES B. ; LEE,DOROTHY B.

Report Date : MAY 1961

Pagination or Media Count : 1

Abstract : Measurements of aerodynamic heat transfer were made at a number of stations along a cone-cylinder-flare model having a 15 degrees total-angle conical nose and a 10 degrees half-angle flare skirt. The maximum Mach number was 4.7, and local Reynolds numbers based on body length to a measurement station varied from 2 x 10 to the 6th power to 138 x 10 to the 6th power. Local Stanton numbers measured on the nose cone and flare showed fair agreement with laminar and turbulent theories, while the measurements on the cylinder were generally somewhat lower than theory. Experimental recovery factors, determined twice during the test, were unaccountably lower than theoretical values. Local transition Reynolds numbers, based on length from the nose tip, varied from 3 x 10 to the 6th power to 18 x 10 to the 6th power and were much lower than values previously obtained on the smoother nose of a similar model. At an angle of attack of about 9 degrees, the heat transfer on the flare increased to more than twie the theoretical turbulent value for zero angle of attack. (Author)

Descriptors :   *AERODYNAMIC HEATING, *BODIES OF REVOLUTION, *CONICAL BODIES, *CYLINDRICAL BODIES, HEAT TRANSFER, HYPERSONIC CHARACTERISTICS, INSTRUMENTATION, MEASUREMENT, ROCKET MODELS, TEMPERATURE, TURBULENT BOUNDARY LAYER

Distribution Statement : APPROVED FOR PUBLIC RELEASE