A Computational Study on the Dynamic Stall of a Flapping Airfoil
Platzer_A_Computational_Study_1998.pdf (624.6Kb)Date
1998Metadata
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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.Collections
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