Preliminary survey of boundary-layer development at a nominal Mach number of 5.5

Harold L. Bloom
naca-rm-e52d03
Jun 1952


Mean skin-friction coefficients on a flat-plate model, with and without initial roughness, and on a wind tunnel wall were measured at a nominal Mach number of 5.5 over a Reynolds number range from 1 X 10(exp 6) to 1 X 10(exp 7), and the results were compared with analytical values.

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