WIND-TUNNEL INVESTIGATION OF TURBULENT BOUNDARY LAYERS ON AXIALLY SYMMETRIC BODIES AT SUPERSONIC SPEEDS
DOUGLAS AIRCRAFT CO LONG BEACH CA
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Characteristics of supersonic turbulent boundary layers were determined for regions of large pressure gradients - both favorable and adverse - and with and without heat transfer. Details of the velocity, temperature, and static-pressure profiles were measured at several stations on three bodies of revolution at Mach numbers from 1.61 to 4.50. Profile data are presented in both graphical and tabular forms. Integrated boundary-layer thicknesses - displacement, momentum, and energy - are presented. The measured growth of the boundary-layer thicknesses is compared with that predicted by two approximate theories.
- Fluid Mechanics