An experimental investigation of the effect of surface heating on boundary-layer transition on a flat plate in supersonic flow

Robert W. Higgins, Constantine C. Pappas
naca-tn-2351
Apr 1951


Wind-tunnel tests have been performed to investigate the effect of surface heating on boundary-layer transition on a flat plate. The tests were performed at a nominal Mach number of 2.40 and a free-stream temperature of -205 degrees F, and the data were obtained at nominal plate temperature levels of 60 degrees (adiabatic recovery temperature), 100, 140, 180, and 260 degrees F over a length Reynolds number range from 0.475 X 10 to the 6th power and 3.93 X 10 to the 6th power.

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