Accession Number : AD0829959
Title : A TECHNIQUE FOR EXPERIMENTAL INVESTIGATION OF HEAT TRANSFER FROM A SURFACE IN SUPERSONIC FLOW AT LARGE SURFACE-TO-FREE-STREAM TEMPERATURE RATIOS.
Descriptive Note : Research note,
Corporate Author : CONVAIR SCIENTIFIC RESEARCH LAB SAN DIEGO CA
Personal Author(s) : Bradfield, W. A. ; Hanson, A. R. ; Sheppard, J. J. ; Larson, R. E.
Report Date : MAY 1958
Pagination or Media Count : 33
Abstract : The experimental technique presented provides a surface of controlled moderately high temperature in a flow of homogeneous and chemically determined gas at high speeds. With this technique it is possible to make detailed temperature and power dissipation surveys over the controlled surface. Detailed Schlieren studies of processes occurring in the boundary layer at the heated surface under these circumstances may be obtained. It is possible to determine mass flux rates from small surface areas with comparatively good accuracy. The present laminar result shows reasonable correlation with the reference enthalpy method of predicting local values of heat flux but the correlation of this data with the theory must be substantiated by additional information. The investigation of heat flux in a region of a strong boundary layer shock wave interaction gives values approximately 4.5 times higher than those predicted by the laminar theory. Surface deterioration studies indicate that a silicon carbide coating on a graphite surface may be a practical inhibitor of surface deterioration at temperatures up to 3200 R in air.
Descriptors : (*CONICAL BODIES, SUPERSONIC CHARACTERISTICS), HEAT TRANSFER, EMISSIVITY, TEST EQUIPMENT, TEST METHODS, WIND TUNNEL MODELS, MODEL TESTS, LAMINAR BOUNDARY LAYER, SHOCK WAVES, FLOW SEPARATION, GRAPHITE, EROSION, SILICON CARBIDES.
Subject Categories : Fluid Mechanics
Distribution Statement : APPROVED FOR PUBLIC RELEASE