Accession Number : AD0638232
Title : EFFECT OF A HIGHLY COOLED WALL ON HYPERSONIC TURBULENT HEAT TRANSFER.
Corporate Author : NAVAL ORDNANCE LAB WHITE OAK MD
Personal Author(s) : Wilson,Donald M. ; Fisher,Paul D.
Report Date : 01 JUN 1966
Pagination or Media Count : 49
Abstract : Turbulent heat-transfer rates were measured on a thin-walled, slender cone in a hypersonic tunnel at a free-stream Mach number of 5.0. Wall-to-stagnation temperature ratios of approximately 0.3 and 0.45 were obtained by cooling the model with liquid CO2. A wide range of test Reynolds numbers were obtained by varying the tunnel supply pressure. This provided data for both laminar and mixed laminar - turbulent boundary-layer conditions. The experimental results are compared with existing theories which predict convective heat-transfer coefficients. These comparisons substantiate the predictions of Winkler and Cha for the present test conditions. (Author)
Descriptors : (*HEAT TRANSFER, *HYPERSONIC FLOW), (*CONICAL BODIES, HEAT TRANSFER), WALLS, COOLING, TURBULENCE, SLENDER BODIES, STAGNATION POINT, HYPERSONIC WIND TUNNELS, REYNOLDS NUMBER, LAMINAR FLOW
Subject Categories : Fluid Mechanics
Distribution Statement : APPROVED FOR PUBLIC RELEASE