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Laser velocimeter measurements of dynamic stallLaser velocimeter measurements were made during the study of a two-dimensional NACA 0012 airfoil undergoing conditions of dynamic stall. The measurements, which were obtained in the Ames 2 foot wind tunnel at reduced frequencies of 0.12 and 1.2, show significant flow field hysteresis around the static stall angle. Comparisons were also made with dual-plate interferograms and good agreement was found for the attached flow cases. For separated flow, characteristic vortex shedding caused poor agreement and significantly increased the measured Reynolds shear stresses.
Document ID
19840026358
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Owen, F. K. (Compass Systems, Inc. San Diego, CA, United States)
Date Acquired
September 4, 2013
Publication Date
April 1, 1984
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.26:166603
NASA-CR-166603
Accession Number
84N34429
Funding Number(s)
PROJECT: RTOP 505-31-21
CONTRACT_GRANT: NAS2-11080
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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