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
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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