A flight investigation of the effect of shape and thickness of the boundary layer on the pressure distribution in the presence of shock

Eziaslav N. Harrin
naca-tn-2765
Sep 1952


An investigation was made in flight at free-stream Mach numbers up to about 0.77 to determine the effect of a laminar boundary layer and thin and thick turbulent boundary layers on the chordwise pressure distribution over an airfoil in the presence of shock at full-scale Reynolds numbers.

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