Accession Number : AD0294193

Title :   THE INFLUENCE OF SHOCK WAVE-BOUNDARY LAYER INTERACTION ON HEAT TRANSFER TO AN AXISYMMETRIC BODY

Corporate Author : CALIFORNIA UNIV BERKELEY INST OF ENGINEERING RESEARCH

Personal Author(s) : HICKMAN,R.S.

Report Date : OCT 1962

Pagination or Media Count : 1

Abstract : The local heat flux to hemisphere cylinder models was measured in the low density wind tunnel. Two different methods were developed and five individual models were tested. Data were obtained throughout the Mach number range of 2 to 6 with Reynolds numbers behind the shock varying from 38.5 to 1720. The stagnation point data were found to agree with continuum boundary layer theory at the higher Reynolds numbers and with Van Dyke's second order boundary layer theory at the lower Reynolds numbers. In addition, the pressure distribution was measured on cooled and uncooled models and was found to agree well with modified Newtonian theory throughout the Reynolds number range. Local recovery factors were also measured over the test Mach number range. A slight slip effect was found to exist near the stagnation point for low Reynolds numbers. (Author)

Descriptors :   *HEAT TRANSFER, *SHOCK WAVES, BOUNDARY LAYER, COOLING, CYLINDRICAL BODIES, FLUID FLOW, HEMISPHERICAL SHELLS, MACH NUMBER, PRESSURE, REYNOLDS NUMBER, WIND TUNNELS

Distribution Statement : APPROVED FOR PUBLIC RELEASE