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Closed-Loop Control of Leading Edge Vorticity on a 3D Wing: Simulations and Low-Dimensional Models

Rowley, Clarence W. and Ahuja, Sunil and Taira, Kunihiko and Colonius, Tim (2008) Closed-Loop Control of Leading Edge Vorticity on a 3D Wing: Simulations and Low-Dimensional Models. In: 38th Fluid Dynamics Conference and Exhibit, 23-26 June 2008, Seattle, WA.

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We study model-based feedback control of the low-Reynolds-number flow over a flat plate at large angles of attack, in both two and three dimensions. Our long-term goal is to be able to manipulate the leading-edge vortices that form on low-aspect-ratio wings at high angles of attack, and that often contribute to exceptionally large lift coefficients. Intwo-dimensional simulations, we present a model-based feedback controller that uses an observer to reconstruct the entire flow field from velocity measurements at three locations, and stabilizes the flow at an angle of attack for which the natural flow state is periodic shedding. In three-dimensional simulations, we use open-loop forcing to study actuator placement, and conclude that trailing-edge actuation is more effective than leading-edge actuation in influencing the forces on the plate, as well as the wake structures. Finally, we present initial results towards extending our model-based control design to the 3D setting, and apply a selective frequency damping method to find unstable equilibrium flow fields in 3D simulations.

Item Type:Conference or Workshop Item (Paper)
Related URLs:
URLURL TypeDescription Paper Paper
Rowley, Clarence W.0000-0002-9099-5739
Taira, Kunihiko0000-0002-3762-8075
Colonius, Tim0000-0003-0326-3909
Additional Information:© 2008 by the authors. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. Published Online: 15 Jun 2012. This work was supported by the AFOSR, grant FA9550-05-1-0369, with program manager Dr. Fariba Fahroo. We gratefully acknowledge Prof. Yannis Kevrekidis for helpful advice about many aspects of this work, especially the selective frequency damping.
Funding AgencyGrant Number
Air Force Office of Scientific Research (AFOSR)FA9550-05-1-0369
Subject Keywords:Fluid Dynamics
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Other Numbering System NameOther Numbering System ID
AIAA Paper2008-3981
Record Number:CaltechAUTHORS:20190717-102320932
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Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:97221
Deposited By: Melissa Ray
Deposited On:19 Jul 2019 17:20
Last Modified:16 Nov 2021 17:29

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