Control of Flow Structure on a Semi-Circular Planform Wing
Abstract
Active flow control is used to modify the lift, drag and pitching moments on a semicircular wing with aspect ratio, AR = 2, and chord Reynolds number is 68,000. The wing is mounted on a pitch/plunge sting mechanism that responds to the instantaneous loads and moments acting on the wing. The leading edge of the airfoil contains 16 spatially localized actuators that can be independently controlled. Smoke wire visualization, surface pressure and six-component force balance measurements are used to characterize the effects of openloop forcing. The lift coefficients on the steady wing are enhanced with the actuation, similar to the effect of dynamic stall vortex lift enhancement that occurs during a pitch up maneuver. Surface pressure measurements are being used to construct a flow model for use in feedback control. Progress toward the goal of designing a feedback controller to stabilize the flight of the model in an oscillatory freestream is discussed.
Additional Information
© 2008 by David R. Williams. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. Published Online: 19 Jun 2012. The support for this work by the U.S. Air Force Office of Scientific Research MURI (FA9550-05-1-0369) with program manager Dr. Fariba Fahroo is gratefully acknowledged. We are also appreciative of the support for Jesse Collins from the Illinois NASA Space Grant Consortium.Attached Files
Published - WilliamsCollinsJankhotEtAl2008.pdf
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Additional details
- Eprint ID
- 97211
- Resolver ID
- CaltechAUTHORS:20190717-102320045
- Air Force Office of Scientific Research (AFOSR)
- FA9550-05-1-0369
- Illinois Space Grant Consortium
- Created
-
2019-07-18Created from EPrint's datestamp field
- Updated
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2021-11-16Created from EPrint's last_modified field
- Other Numbering System Name
- AIAA Paper
- Other Numbering System Identifier
- 2008-597