Actions for Unsteady flow past an airfoil pitched at constant rate

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Unsteady flow past an airfoil pitched at constant rate

Author
Lourenco, L.
Published
Mar 1, 1992.
Physical Description
1 electronic document
Additional Creators
Vandommelen, L., Shib, C., and Krothapalli, A.
Online Version

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Unclassified, Unlimited, Publicly available.
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Summary
The unsteady flow past a NACA 0012 airfoil that is undertaking a constant-rate pitching up motion is investigated experimentally by the PIDV technique in a water towing tank. The Reynolds number is 5000, based upon the airfoil's chord and the free-stream velocity. The airfoil is pitching impulsively from 0 to 30 deg. with a dimensionless pitch rate alpha of 0.131. Instantaneous velocity and associated vorticity data have been acquired over the entire flow field. The primary vortex dominates the flow behavior after it separates from the leading edge of the airfoil. Complete stall emerges after this vortex detaches from the airfoil and triggers the shedding of a counter-rotating vortex near the trailing edge. A parallel computational study using the discrete vortex, random walk approximation has also been conducted. In general, the computational results agree very well with the experiment.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19940030463.
Accession ID: 94N34969.
NASA. Ames Research Center, Physics of Forced Unsteady Separation; p 35-59.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15658175