Show/Hide Menu
Hide/Show Apps
anonymousUser
Logout
Türkçe
Türkçe
Search
Search
Login
Login
OpenMETU
OpenMETU
About
About
Open Science Policy
Open Science Policy
Communities & Collections
Communities & Collections
Help
Help
Frequently Asked Questions
Frequently Asked Questions
Videos
Videos
Thesis submission
Thesis submission
Publication submission with DOI
Publication submission with DOI
Publication submission
Publication submission
Contact us
Contact us
Computational study of flapping airfoil aerodynamics
Date
2000-05-01
Author
Tuncer, İsmail Hakkı
Platzer, MF
Metadata
Show full item record
This work is licensed under a
Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License
.
Item Usage Stats
5
views
0
downloads
Cite This
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.
Subject Keywords
Aerospace Engineering
URI
https://hdl.handle.net/11511/42297
Journal
JOURNAL OF AIRCRAFT
DOI
https://doi.org/10.2514/2.2628
Collections
Department of Aerospace Engineering, Article
Citation Formats
IEEE
ACM
APA
CHICAGO
MLA
BibTeX
İ. H. Tuncer and M. Platzer, “Computational study of flapping airfoil aerodynamics,”
JOURNAL OF AIRCRAFT
, vol. 37, no. 3, pp. 514–520, 2000, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/42297.