Experimental Investigation of Separation Control on a NACA0024 Airfoil using Stationary and Non-Stationary AC-Dielectric Barrier Discharge Plasma Actuator


1 Department of Engineering, Zanjan Branch, Islamic Azad University, Zanjan, Iran

2 Department of Earth System Science, University of California Irvine, Irvine, CA 92697-3100, USA

3 Department of Aerospace Engineering, K.N. Toosi University of Technology, Tehran, Iran

4 Department of Mechanical Engineering, University of Tabriz, Tabriz, Iran

5 New Technologies Engineering Faculty, Shahid Beheshti University, Tehran, Iran

6 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.