G. Tathiri - Department of Engineering, Zanjan Branch, Islamic Azad University, Zanjan, Iran
H. Parishani - Department of Earth System Science, University of California Irvine, Irvine, CA ۹۲۶۹۷-۳۱۰۰, USA
S. G. Pouryoussefi - Department of Aerospace Engineering, K.N. Toosi University of Technology, Tehran, Iran
E. Esmaeilzadeh - Department of Mechanical Engineering, University of Tabriz, Tabriz, Iran
S. M. Mirsajedi - New Technologies Engineering Faculty, Shahid Beheshti University, Tehran, Iran
M. Mirzaei - Department of Aerospace Engineering, K.N. Toosi University of Technology, Tehran, Iran
N. Khatibzadeh - Beckman Laser Institute and Medical Clinic, Irvine, CA ۹۲۶۱۲, USA

An experimental study of stationary and non-stationary dielectric barrier discharge (DBD) plasma actuator is presented to control the flow around a NACA۰۰۲۴ airfoil. First, an induced air velocity of ~۵ 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 NACA۰۰۲۴ airfoil at Reynolds number of ۰.۴۸×۱۰۶, we are able to increase the stall angle of the airfoil to ۱۸º, compared to ۱۶º in no-actuator state. Furthermore, during the plasma actuation, the lift is increased by up to ۵%. We show that non-stationary actuation, while yielding a performance similar to stationary actuation, leads to a considerable reduction of ~۵۱% in plasma power consumption.

Flow control, Induced flow, NACA۰۰۲۴ Airfoil, DBD plasma actuator, Separation point