Experimental investigation of heat transfer through laminar and turbulent boundary layers on a cooled flat plate at a mach number of 2.4

Ellis G. Slack
naca-tn-2686
Apr 1952


Wind-tunnel tests of the heat-transfer characteristics of the laminar and turbulent boundary layers on a cooled flat plate were conducted at a nominal Mach number of 2.4. Data were obtained for a Reynolds number range of 1.5 X 10(5) to 3 X 10(6) and for nominal surface temperatures of -40 degrees F to 45 degrees F with recovery temperatures of the order of 65 degrees F.

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