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A Computational Study on the Dynamic Stall of a Flapping Airfoil

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Author
Tuncer, Ismail
Walz, Ralf
Platzer, Max F.
Date
1998
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Abstract
The 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.
Description
The article of record as published may be found at http://dx.doi.org/10.2514/6.1998-2519
Rights
This 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.
URI
http://hdl.handle.net/10945/50285
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    On the Prediction of Dynamic Stall Onset on Airfoils in Low Speed Flow 

    Jones, K.D.; Platzer, M.F. (1998);
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    A Fast Method for the Prediction of Dynamic Stall Onset on Turbomachinery Blades 

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    Jet Characteristics of a Plunging Airfoil 

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    Water-tunnel tests of a NACA 0012 airfoil that was oscillated sinusoidally in plunge are described. The flowfield downstream of the airfoil was explored by dye flow visualization and single-component laser Doppler velocimetry ...
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