Experimental investigation at a Mach number of 2.41 of average skin-friction coefficients

Robert M. O Donnell
naca-tn-3122
Jan 1954


and velocity profiles for laminar and turbulent boundary layers and an assessment of probe effects An experimental investigation was made of laminar and turbulent boundary layers on the outer surface of a hollow cylinder at a Mach number of 2.41 and over a Reynolds number range of 0.06 X 10(exp 6) to 0.95 X 10(exp 6) per inch. Boundary-layer surveys were made by means of a total-pressure probe for stations ranging from 0.58 to 8.08 inches from the leading edge.

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