Separated Flow Control with Actuated Membrane Wings

By perturbing shear layer instabilities, some level of control over highly separated flows can be established, as has been demonstrated on rigid wings using synthetic jet actuators or acoustic excitation. Here, we demonstrate similar phenomena using sinusoidal actuation of a dielectric membrane wing. The effect of actuation on lift is examined as a function of freestream velocity (5-25 m/s), angle of attack (10$^\circ$-40$^\circ$), and actuation frequency ($0.1

To cite this abstract, use the following reference: http://meetings.aps.org/link/BAPS.2017.DFD.M16.7