Feedback Control of High-Lift State for A Low-Aspect-Ratio Wing
Abstract
The objective of this study is to employ feedback control to maximize time-average lift on a low-aspect-ratio wing by directly modifying the three-dimensional dynamics of the wake vortices. Flow control around such wing at post-stall angles of attack is numerically investigated at a low Reynolds number of 300 with blowing along the trailing edge. Motivated by the existence of time-periodic high-lift states under open-loop control with periodic excitation, the extremum seeking algorithm is considered for designing feedback control to lock the flow onto such high-lift states. Preliminary results are presented where the close-loop control is able to seek the optimal actuation frequency and yield high lift.
Additional Information
© 2010 by the authors. Published by the American Institute of Aeronautics and Astronautics, Inc. with permission. Published Online: 25 Jun 2012. This work was supported by the US Air Force Office of Scientific Research (FA9550-05-1-0369) with the computations made possible by the US Department of Defense HPCMP and the Princeton University TIGRESS programs. Helpful discussions with Prof. David Williams and Mr. Steven Brunton are greatly acknowledged.Attached Files
Submitted - TairaRowleyColonius2010.pdf
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Additional details
- Eprint ID
- 97212
- Resolver ID
- CaltechAUTHORS:20190717-102320131
- Air Force Office of Scientific Research (AFOSR)
- FA9550-05-1-0369
- Created
-
2019-07-18Created from EPrint's datestamp field
- Updated
-
2021-11-16Created from EPrint's last_modified field
- Other Numbering System Name
- AIAA Paper
- Other Numbering System Identifier
- 2010-357