Accession Number : AD0445121

Title :   HIGH TEMPERATURE TURBULENT HEAT-TRANSFER MEASUREMENTS,

Corporate Author : NAVAL ORDNANCE LAB WHITE OAK MD

Personal Author(s) : Noonan, Barry J. ; Rand, James L.

Report Date : 20 JAN 1964

Pagination or Media Count : 10

Abstract : Turbulent heat-transfer rates through a highly cooled boundary layer have been investigated experimentally by testing in the throat region of a reflected shock tunnel. Local heat-transfer measurements were made in a constant diameter pipe, simulating a flat plate, with extreme free-stream conditions. Unit Reynolds number, on the order of 3 x 10 to the 7th power/ft, stagnation enthalpies approaching 8,000 Btu/lb, free-stream temp up to 8,000 K, and free-stream pressure of about 100 atm were generated by the shock tunnel for these experiments. Heat-transfer rates in the neighborhood of 50,000 Btu/sq ft sec were measured by means of a ring-type calorimeter heat-transfer gage developed at the Naval Ordnance Laboratory. Experimental results are compared with some existing empirical methods for predicting convective heat-transfer coefficients. It is concluded that the experimental data substantiate some of the empirical predictions for the given test conditions. (Author)

Descriptors :   (*AERODYNAMIC HEATING, TURBULENT BOUNDARY LAYER), (*HEAT TRANSFER, TURBULENT BOUNDARY LAYER), (*TURBULENT BOUNDARY LAYER, HEAT TRANSFER), HIGH TEMPERATURE, CALORIMETERS, STAGNATION POINT, TURBULENCE, MEASUREMENT, EQUATIONS, MATHEMATICAL PREDICTION.

Distribution Statement : APPROVED FOR PUBLIC RELEASE