Department of Engineering, Zanjan Branch, Islamic Azad University, Zanjan, Iran
Department of Earth System Science, University of California Irvine, Irvine, CA 92697-3100, USA
Department of Aerospace Engineering, K.N. Toosi University of Technology, Tehran, Iran
Department of Mechanical Engineering, University of Tabriz, Tabriz, Iran
New Technologies Engineering Faculty, Shahid Beheshti University, Tehran, Iran
Beckman Laser Institute and Medical Clinic, Irvine, CA 92612, USA
An experimental study of stationary and non-stationary dielectric barrier discharge (DBD) plasma actuator is presented to control the flow around a NACA0024 airfoil. First, an induced air velocity of ~5 m/s is generated on a flat plate in still air using an AC-DBD actuator to find the optimal setup of the actuator (voltage, frequency, electrode width and gap size). Using the same actuator in the optimal position/setup on a NACA0024 airfoil at Reynolds number of 0.48×106, we are able to increase the stall angle of the airfoil to 18º, compared to 16º in no-actuator state. Furthermore, during the plasma actuation, the lift is increased by up to 5%. We show that non-stationary actuation, while yielding a performance similar to stationary actuation, leads to a considerable reduction of ~51% in plasma power consumption.