Accession Number : AD0291819
Title : SUPERSONIC TURBULENT BOUNDARY LAYER GROWTH OVER COOLED WALLS IN ADVERSE PRESSURE GRADIENTS
Descriptive Note : Final report.
Corporate Author : UNITED TECHNOLOGIES CORP HARTFORD CT
Personal Author(s) : KEPLER, C E ; OBRIEN, R L
PDF Url : AD0291819
Report Date : Oct 1962
Pagination or Media Count : 119
Abstract : The characteristics of supersonic turbulent boundary layers on cooled surfaces having adverse pressure gradients were investigated to provide design information for hypersonic inlets. Tests were conducted at Mach numbers of 3 and 6 with values of wall temperature as low as 30% of the adiabatic recovery temperature. The adverse pressure gradients were generated by two-dimensional model including a circular-arc surface, an isentropic-compression surface, and an oblique shock generator. Velocity and temperature profiles through the boundary layer were obtained and the integral boundary layer parameters were evaluated along the surface. An analytical investigation was also conducted to provide a basis for evaluating the experimental results. It was found that cooled, turbulent boundary layers in adverse pressure gradients are thinner and less distorted than uncooled boundary layers, that the ratio of Stanton number to skin-friction coefficient is higher than the flat-plate value, and t at the total amount of heat removed is greater than that predicted by integrating local heat-transfer rates based on flat-plate conditions al ng the surface.
Descriptors : *TURBULENT BOUNDARY LAYER, BOUNDARY LAYER, COOLING, GROWTH(PHYSIOLOGY), HEAT TRANSFER, HYPERSONIC NOZZLES, METAL PLATES, PRESSURE, SHOCK WAVES, SUPERSONIC WIND TUNNELS, TEMPERATURE, TEST METHODS, WIND TUNNEL NOZZLES
Subject Categories : Fluid Mechanics
Distribution Statement : APPROVED FOR PUBLIC RELEASE