Accession Number : AD0264028

Title :   FREE-FLIGHT INVESTIGATION OF HEAT TRANSFER TO AN UNSWEPT CYLINDER SUBJECTED TO AN INCIDENT SHOCK AND FLOW INTERFERENCE FROM AN UPSTREAM BODY AT MACH NUMBERS UP TO 5.50

Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON D C

Personal Author(s) : CARTER,HOWARD S. ; CARR,ROBERT E.

Report Date : OCT 1961

Pagination or Media Count : 1

Abstract : Heat-transfer rates were measure in free flightALONG THE STAGNATION LINE OF AN UNSWEPT CYLINDER MOUNTED TRANSVERSELY ON AN AXIAL CYLINDER SO THAT THE SHOCK WAVE FROM THE HEMISPHERICAL NOSE OF THE AXIAL CYLINDER INTERSECTED THE BOW SHOCK OF THE UNSWEPT TRANSVERSE CYLINDER. Data were obtained at Mach numbers from 2.53 to 5.50 and at Reynolds numbers based on the transverse cylinder diameter from 1.00 x 10 to the sixth power to 1.87 x 10 to the sixth power. Shadowgraph pictures made in a wind tunnel showed that the flow field was influenced by boundary-layer separation on the axial cylinder and by end effects on the transverse cylinder as well as by the intersecting shock . Under these conditions, the measured heat-transfer rates had inconsistent variations both in agnitude and distribution which precluded separating the effects of these disturbances. The general magnitude of the measured heating rates at Mach numbers up to 3 was from 0.1 to 0.5 of the theoretical laminar heating rates along the stagnation line for an infinite unswept cylinder in undisturbed flow. (Author)

Descriptors :   *AERODYNAMIC HEATING, *HEAT TRANSFER, *HYPERSONIC FLOW, *SUPERSONIC FLOW, AERODYNAMIC CHARACTERISTICS, AERODYNAMIC CONFIGURATIONS, BLUNT BODIES, CYLINDRICAL BODIES, FLUID MECHANICS, GUIDED MISSILES, SPACECRAFT

Distribution Statement : APPROVED FOR PUBLIC RELEASE