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dc.contributor.authorTuncer, Ismail
dc.contributor.authorWalz, Ralf
dc.contributor.authorPlatzer, Max F.
dc.date1998
dc.date.accessioned2016-10-14T15:10:26Z
dc.date.available2016-10-14T15:10:26Z
dc.date.issued1998
dc.identifier.citationTuncer, Ismail H., Ralf Walz, and Max F. Platzer. "A computational study on the dynamic stall of a flapping airfoil." AIAA paper 2519 (1998): 1998.en_US
dc.identifier.urihttps://hdl.handle.net/10945/50285
dc.descriptionThe article of record as published may be found at http://dx.doi.org/10.2514/6.1998-2519en_US
dc.description.abstractThe dynamic stall boundaries of a NACA 0012 airfoil oscillating in either the pure plunge mode or in the combined pitch and plunge mode is computed using a thin-layer Navier-Stokes solver. Unsteady flowfields are computed at the free-stream Mach number of 0.3, the Reynolds number of 1 • 106, and the Baldwin-Lomax turbulence model is employed. It is found that the pure plunge oscillation leads to dynamic stall as soon as the non-dimensional plunge velocity exceeds the approximate value of 0.35. In addition, the power extraction capability of the airfoil operating in the wingmill mode is studied by computing the dynamic stall boundary for a combined pitch and plunge motion at the reduced frequency values of 0.1, 0.25 and 0.5.en_US
dc.description.sponsorshipNaval Research Laboratoryen_US
dc.format.extent7 p.en_US
dc.publisherAmerican Institute of Aeronautics and Astronautics, Inc.en_US
dc.rightsThis publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.en_US
dc.titleA Computational Study on the Dynamic Stall of a Flapping Airfoilen_US
dc.typeArticleen_US
dc.contributor.corporateNaval Postgraduate School (U.S.)en_US
dc.description.funderNaval Research Laboratoryen_US


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