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A laser velocimeter flow survey above a stalled wingA laser velocimeter operating in the backscatter mode was used to survey the flow about a stalled wing installed in the Langley V/STOL tunnel. Mean velocities and magnitudes of velocity fluctuations were calculated from measurements of two orthogonal components of velocity. Free shear mixing layers above and below a large separated flow region were defined. Velocity power spectra were calculated at two points in the flow field. The flow-field survey was carried out about a rectangular aspect-ratio-8 wing with an airfoil section. The wing angle of attack was 19.4 deg, the Mach number was 0.148, and the nominal Reynolds number was 1 x 1 million.
Document ID
19790005848
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Young, W. H., Jr. (NASA Langley Research Center Hampton, VA, United States)
Meyers, J. F. (NASA Langley Research Center Hampton, VA, United States)
Hoad, D. R. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 3, 2013
Publication Date
December 1, 1978
Subject Category
Aerodynamics
Report/Patent Number
NASA-TP-1266
AVRADCOM-TR-78-50
Accession Number
79N14019
Funding Number(s)
PROJECT: DA PROJ. 1L1-61102-AH-45
PROJECT: RTOP 505-10-23-00
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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