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In-flight boundary-layer measurements on a hollow cylinder at a Mach number of 3.0Skin temperatures, shear forces, surface static pressures, boundary layer pitot pressures, and boundary layer total temperatures were measured on the external surface of a hollow cylinder that was 3.04 meters long and 0.437 meter in diameter and was mounted beneath the fuselage of the YF-12A airplane. The data were obtained at a nominal free stream Mach number of 3.0 (a local Mach number of 2.9) and at wall to recovery temperature ratios of 0.66 to 0.91. The local Reynolds number had a nominal value of 4,300,000 per meter. Heat transfer coefficients and skin friction coefficients were derived from skin temperature time histories and shear force measurements, respectively. In addition, boundary layer velocity profiles were derived from pitot pressure measurements, and a Reynolds analogy factor was obtained from the heat transfer and skin friction measurements. The measured data are compared with several boundary layer prediction methods.
Document ID
19810003850
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Quinn, R. D. (NASA Hugh L. Dryden Flight Research Center Edwards, CA, United States)
Gong, L. (NASA Hugh L. Dryden Flight Research Center Edwards, CA, United States)
Date Acquired
September 4, 2013
Publication Date
November 1, 1980
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
H-1101
NASA-TP-1764
Accession Number
81N12361
Funding Number(s)
PROJECT: RTOP 505-43-24
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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