Accession Number : AD0432218


Title :   WIND TUNNEL TESTS AT SUPERSONIC MACH NUMBERS TO DETERMINE HEAT-TRANSFER COEFFICIENTS IN THE SHOCK WAVE-BOUNDARY LAYER INTERACTION REGION ON A PLANE SURFACE,


Corporate Author : UNIVERSITY OF SOUTHERN CALIFORNIA LOS ANGELES ENGINEERING CENTER


Personal Author(s) : Kelley,Lawrence R


Report Date : 27 Dec 1962


Pagination or Media Count : 31


Abstract : The objective was to provide experimentallydetermined heat transfer coefficients on a flatplate model to find a correlation between the heat transfer coefficients in the shock waveboundary layer interaction zone and such quantities as the effective Reynolds number, the free stream Mach number, and the strength of the wave. The tests were conducted at Mach 3.0 and 5.0 in two different wind tunnel circuits. The Mach 3.0 tests were performed using the Mach 3-4 variablegeometry nozzle, while the Mach 5.0 tests were performed with the Mach 4-6 variable-geometry nozzle. Both of these wind tunnel circuits have test sections approximately 21.5 inches square. Heat transfer coefficients at several stations were determined by measuring the amount of electrical power input required by nickel-chrome heating elements to maintain a given equilibrium temperature on the elements. The measurement was made for three or four different equilibrium temperatures, and the rate of change of power input with respect to the equilibrium temperature was then used to represent the heat transfer coefficient at that given station. (Author)


Descriptors :   *AERODYNAMIC HEATING , HEAT TRANSFER COEFFICIENTS , FLAT PLATE MODELS , SHOCK WAVES , SUPERSONIC CHARACTERISTICS , BOUNDARY LAYER TRANSITION , MODEL TESTS , INSTRUMENTATION , REYNOLDS NUMBER


Distribution Statement : APPROVED FOR PUBLIC RELEASE