Computational Study of Flapping Airfoil Aerodynamics
Authors
Tuncer, Ismail H.
Platzer, Max F.
Subjects
Advisors
Date of Issue
2000
Date
May-June 2000
Publisher
Language
Abstract
Unsteady, viscous, low-speed flows over a NACA 0012 airfoil oscillated in plunge and/or pitch at various reduced frequency, amplitude, and phase shift are computed. Vortical wake formations, boundary-layer flows at the leading edge, the formation of leading-edge vortices and their downstream convection are presented in terms of unsteady particle traces. Flow separation characteristics and thrust-producing wake profiles are identified. Computed results compare well with water tunnel flow visualization and force data and other computational data. The maximum propulsive efficiency is obtained for cases where the flow remains mostly attached over the airfoil oscillated in a combined pitch and plunge.
Type
Article
Description
The article of record as published may be found at http://dx.doi.org/10.2514/2.2628
Series/Report No
Department
Organization
Naval Postgraduate School (U.S.)
Identifiers
NPS Report Number
Sponsors
National Research Laboratory
Funder
National Research Laboratory
Format
10 p.
Citation
JOURNAL OF AIRCRAFT
Vol. 37, No. 3, May–June 2000
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.