Accession Number : AD0261699

Title :   MEASUREMENTS OF AERODYNAMIC HEAT TRANSFER AND BOUNDARY-LAYER TRANSITION ON A 15 DEGREE CONE IN FREE FLIGHT AT SUPERSONIC MACH NUMBERS UP TO 5.2,

Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON D C

Personal Author(s) : Rumsey ,Charles B. ; Lee,Dorothy B.

Report Date : AUG 1961

Pagination or Media Count : 43

Abstract : Measurements of aerodynamic heat transfer have been made at several stations on the 15 degree total-angle conical nose of a rocket-propelled model in free flight at Mach numbers up to 5.2. Data are presented for a range of local Mach number just outside the boundary layer from 1.40 to 4.65 and a range of local Reynolds number from 3.8 times 10 to the 6th power to 46.5 times 10 to the 6th power, based on length from the nose tip to a measurement station. Laminar, transitional, and turbulent heat-transfer coefficients were measured. The laminar data were in agreement with laminar theory for cones, and the turbulent data agreed well with turbulent theory for cones using Reynolds number based on length from the nose tip. (Author)

Descriptors :   *AERODYNAMIC CHARACTERISTICS, *AERODYNAMIC HEATING, *CONICAL BODIES, *HYPERSONIC CHARACTERISTICS, *SUPERSONIC FLOW, AERODYNAMIC CONFIGURATIONS, BODIES OF REVOLUTION, BOUNDARY LAYER, HEAT TRANSFER, LAMINAR BOUNDARY LAYER, MEASUREMENT, MODEL TESTS, REYNOLDS NUMBER, TURBULENT BOUNDARY LAYER

Distribution Statement : APPROVED FOR PUBLIC RELEASE