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Donaldson, Coleman Dup

Publications and source records attributed to Donaldson, Coleman Dup.

Study of the Pressure Rise Across Shock Waves Required to Separate Laminar and Turbulent Boundary Layers

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.

FLOW, SUPERSONIC↗