CaltechAUTHORS
Published April 13, 2011 | Version public
Journal Article Metadata-only

Control of vortex shedding on two- and three-dimensional aerofoils

Creators

  • 1. ROR icon California Institute of Technology
  • 2. ROR icon Illinois Institute of Technology

Abstract

We review and expand on the control of separated flows over flat plates and aerofoils at low Reynolds numbers associated with micro air vehicles. Experimental observations of the steady-state and transient lift response to actuation, and its dependence on the actuator, aerofoil geometry and flow conditions, are discussed and an attempt is made to unify them in terms of their excitation of periodic and transient vortex shedding. We also examine strategies for closed-loop flow and flight control using actuation of leading-edge vortices.

Additional Information

© 2011 The Royal Society. One contribution of 15 to a Theme Issue 'Flow-control approaches to drag reduction in aerodynamics: progress and prospects'. Our work was supported by the US AFOSR under grants FA9550-05-1-0369 and FA9550-09-1-0189. We wish to thank Prof. Clancy Rowley, Prof. Gilead Tadmor, Mr Vien Quach and Mr Wesley Kerstens for their important contributions. We are also indebted to Prof. Rudibert King for his important contributions in developing the closed-loop controllers.

Additional details

Identifiers

Eprint ID
23120
DOI
10.1098/rsta.2010.0355
Resolver ID
CaltechAUTHORS:20110328-100709222

Related works

Describes
10.1098/rsta.2010.0355 (DOI)

Funding

Air Force Office of Scientific Research (AFOSR)
FA9550-05-1-0369
Air Force Office of Scientific Research (AFOSR)
FA9550-09-1-0189

Dates

Created
2011-03-29
Created from EPrint's datestamp field
Updated
2021-11-09
Created from EPrint's last_modified field