Accession Number : AD0617622

Title :   AN EXPERIMENTAL INVESTIGATION OF THE NEAR WAKE OF A SLENDER CONE AT MACH NUMBER =8 AND 12,

Corporate Author : POLYTECHNIC INST OF BROOKLYN N Y

Personal Author(s) : Cresci,Robert J. ; Zakkay,Victor

Report Date : MAY 1965

Pagination or Media Count : 54

Abstract : Various experimental data were obtained in the near wake region of a 10 degree angle sharp cone at free stream Mach numbers of 8.0 and 11.8. The Mach 8.0 tests were conducted at free stream Reynolds numbers of 300,000 and 1,700,000 per foot; laminar and turbulent boundary layers were obtained on the cone surface at these respective Reynolds numbers. Data obtained include radial profiles of temperature, pressure, and Mach number at axial locations between one and three base diameters downstream of the model. Heat transfer and pressure distributions on the model base were also obtained. The Mach 11.8 tests were conducted at a free stream Reynolds number of 600,000 per foot and the surface boundary layer for all these tests were laminar. Data obtained include centerline distributions of Mach number, pressure, and temperature for a distance between one and four base diameters downstream of the model. Centerline temperatures were also obtained in the recirculation region for model wall to stagnation temperature ratios of 0.06 and 0.47. In addition, total temperature profiles were obtained downstream of the rear stagnation point. (Author)

Descriptors :   (*SLENDER BODIES, HYPERSONIC CHARACTERISTICS), (*CONICAL BODIES, HYPERSONIC CHARACTERISTICS), WAKE, STAGNATION POINT, AERODYNAMIC HEATING, HEAT TRANSFER, LAMINAR BOUNDARY LAYER, TURBULENT BOUNDARY LAYER, PRESSURE

Distribution Statement : APPROVED FOR PUBLIC RELEASE