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Flapping wing propulsion offers unrivalled manoeuvrability and efficiency atlow flight speeds and in hover. These advantages are attributed to the leadingedge vortex developing on an unsteady wing, which induces additional lift. Wepropose and validate a manipulation hypothesis that allows prolongation of theleading edge vortex growth phase, by delaying its detachment with the aid offlow control. This approach targets an overall lift increase on unsteadyairfoils. A dielectric barrier discharge plasma actuator is successfully usedto compress secondary structures upstream of the main vortex on a pitching andplunging flat plate. To determine flow control timing and location, thetangential velocity on the airfoil surface is used, which is also used toquantify topological effects of flow control. This flow control is then testedfor different motion kinematics and on a NACA 0012 airfoil. Significantincrease of the peak circulation of the leading edge vortex of about 20% forall cases with flow control indicates that this approach is applicable forvarious kinematics, dynamics and airfoil types.

Delaying Leading Edge Vortex Detachment by Plasma Flow Control at Topologically Critical Locations