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Experimental study of the separating confluent boundary-layer. Volume 2: Experimental dataAn experimental low speed study of the separating confluent boundary layer on a NASA GAW-1 high lift airfoil is described. The airfoil was tested in a variety of high lift configurations comprised of leading edge slat and trailing edge flap combinations. The primary test instrumentation was a two dimensional laser velocimeter (LV) system operating in a backscatter mode. Surface pressures and corresponding LV derived boundary layer profiles are given in terms of velocity components, turbulence intensities and Reynolds shear stresses as characterizing confluent boundary layer behavior up to and beyond stall. LV derived profiles and associated boundary layer parameters and those obtained from more conventional instrumentation such as pitot static transverse, Preston tube measurements and hot-wire surveys are compared.
Document ID
19840012413
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Braden, J. A. (Lockheed-Georgia Co. Marietta, GA, United States)
Whipkey, R. R. (Lockheed-Georgia Co. Marietta, GA, United States)
Jones, G. S. (Lockheed-Georgia Co. Marietta, GA, United States)
Lilley, D. E. (Lockheed-Georgia Co. Marietta, GA, United States)
Date Acquired
September 4, 2013
Publication Date
March 1, 1983
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-166018
NAS 1.26:166018
LG82ER0184
Accession Number
84N20481
Funding Number(s)
CONTRACT_GRANT: NAS1-16028
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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