Effect of Tip Vortices in Low-Reynolds-Number Poststall Flow Control
- Creators
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Taira, Kunihiko
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Colonius, Tim
Abstract
We numerically investigate the application of steady blowing to three-dimensional stalled flows around low-aspect-ratio rectangular flat-plate wings at a Reynolds number of 300. The objective of this study is to explore techniques to enhance lift by directly modifying the dynamics of the wake vortices. Out of various combinations of forcing location and direction considered, we identify two configurations that provide significant lift enhancement. In these cases, actuation appears to strengthen the tip vortices for increased downward induced velocity upon the leading-edge vortices. This in turn moves the low-pressure core directly above the top surface of the wing to greatly enhance lift.
Additional Information
© 2008 by the authors. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. Presented as Paper 376 at the 47th AIAA Aerospace Sciences Meeting, Orlando, FL, 5–8 January 2009; received 26 August 2008; revision received 4 December 2008; accepted for publication 5 December 2008. This work was supported by the U.S. Air Force Office of Scientific Research (FA9550-05-1-0369), with some of the computations made possible by the U.S. Department of Defense High Performance Computing Modernization Program. We are thankful to Clarence W. Rowley, Morteza Gharib, David R. Williams, Gilead Tadmor, and William B. Dickson for the enlightening discussions.Attached Files
Published - Taira2009p63910.25141.40615.pdf
Erratum - TairaColonius2010.pdf
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Additional details
- Eprint ID
- 16228
- Resolver ID
- CaltechAUTHORS:20091009-082632397
- FA9550-05-1-0369
- Air Force Office of Scientific Research (AFOSR)
- Created
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2009-10-19Created from EPrint's datestamp field
- Updated
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2023-06-01Created from EPrint's last_modified field