A Computational Study on the Dynamic Stall of a Flapping Airfoil
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Authors
Tuncer, Ismail
Walz, Ralf
Platzer, Max F.
Subjects
Advisors
Date of Issue
1998
Date
1998
Publisher
American Institute of Aeronautics and Astronautics, Inc.
Language
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.
Type
Article
Description
The article of record as published may be found at http://dx.doi.org/10.2514/6.1998-2519
Series/Report No
Department
Organization
Naval Postgraduate School (U.S.)
Identifiers
NPS Report Number
Sponsors
Naval Research Laboratory
Funder
Naval Research Laboratory
Format
7 p.
Citation
Tuncer, Ismail H., Ralf Walz, and Max F. Platzer. "A computational study on the dynamic stall of a flapping airfoil." AIAA paper 2519 (1998): 1998.
Distribution Statement
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.