Accession Number : AD0018797

Title :   LOCAL FLOW CONDITIONS RECOVERY FACTORS AND HEAT-TRANSFER COEFFICIENTS ON THE NOSE OF A HEMISPHERE-CYLINDER AT A MACH NUMBER OF 2.8

Corporate Author : NAVAL ORDNANCE LAB WHITE OAK MD

Personal Author(s) : KOROBKIN,IRVING

Report Date : 05 MAY 1953

Pagination or Media Count : 13

Abstract : Local flow conditions, recovery factors, and heat-transfer coefficients were determined experimentally on the hemispheric nose of a hemisphere-cylinder with a laminar boundary layer at M=2.8. Results indicated that the recovery factor may be expressed by the square root of the Prandtl number even in the presence of a pressure gradient. An analysis of the supersonic heat-transfer data revealed that the supersonic values obey a law almost identical to that derived from incompressible theory.

Descriptors :   FLOW, HEAT TRANSFER, HEAT TRANSFER COEFFICIENTS, HEMISPHERES, INCOMPRESSIBILITY, LAMINAR BOUNDARY LAYER, NOSES, PRANDTL NUMBER, PRESSURE GRADIENTS, RECOVERY, SQUARE ROOTS, SUPERSONIC CHARACTERISTICS, THEORY, VALUE.

Distribution Statement : APPROVED FOR PUBLIC RELEASE