Study of the pressure rise across shock waves required to separate laminar and turbulent boundary layers

Donaldson, Coleman Dup Lange, Roy H
naca-tn-2770
September 1952


Results are presented of a dimensional study and an experimental investigation of the pressure rise across a shock wave which causes separation of the boundary layer on a flat plate. The experimental part of the investigation was conducted at a Mach number of 3.03 for a Reynolds number range of 2 x 10 (sup) 6 to 19 x 10 (sup) 6. The available experimental data are compared with the predictions of the present study, and the significance of the results obtained is discussed relative to certain practical design problems.

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