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Analysis of oscillatory pressure data including dynamic stall effectsThe dynamic stall phenomenon was examined in detail by analyzing an existing set of unsteady pressure data obtained on an airfoil oscillating in pitch. Most of the data were for sinusoidal oscillations which penetrated the stall region in varying degrees, and here the effort was concentrated on the chordwise propagation of pressure waves associated with the dynamic stall. It was found that this phenomenon could be quantified in terms of a pressure wave velocity which is consistently much less than free-stream velocity, and which varies directly with frequency. It was also found that even when the stall region has been deeply penetrated and a substantial dynamic stall occurs during the downstroke, stall recovery near minimum incidence will occur, followed by a potential flow behavior up to stall inception.
Document ID
19740017427
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Carta, F. O. (United Aircraft Corp. East Hartford, CT, United States)
Date Acquired
September 3, 2013
Publication Date
May 1, 1974
Publication Information
Publisher: NASA
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-2394
Accession Number
74N25540
Funding Number(s)
CONTRACT_GRANT: NAS1-11977
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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