The boundary layer on a turbine nozzle blade was investigated with an optical interferometer over a range of Reynolds numbers and subsonic downstream Mach numbers. The ratio of laminar boundary-layer thickness to distance downstream from the minimum pressure point on the suction side of the blade was found to be essentially a unique function of a length Reynolds number based on this distance. Thickness critical Reynolds numbers for transition increased, with throat Reynolds number, from 3000 to 9000 on the suction side and from 1200 to 3100 on the pressure side. A laminar velocity profile was computed from a density profile measured at a point of zero pressure gradient, and satisfactory agreement with theoretical profiles was obtained.

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