Author/Authors :
Tathiri، G. نويسنده Department of Engineering,Islamic Azad University, Zanjan Branch,Zanjan,Iran , , Mirzaei، M. نويسنده Department of Aerospace Engineering,K.N. Toosi University of Technology,Tehran,Iran , , Khatibzadeh، N. نويسنده Beckman Laser Institute and Medical Clinic,Irvine,USA , , Parishani، H. نويسنده Department of Earth System Science,University of California Irvine,Irvine,USA , , Pouryoussefi، S. G. نويسنده Department of Aerospace Engineering,K.N. Toosi University of Technology,Tehran,Iran , , Esmaeilzadeh، E. نويسنده Department of Mechanical Engineering,University of Tabriz,Tabriz,Iran , , Mirsajedi، S. M. نويسنده New Technologies Engineering Faculty,Shahid Beheshti University,Tehran,Iran ,
Abstract :
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 0.48×10^6, we are able to increase the stall angle of the airfoil to
18°, compared to 16° 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.
Keywords :
DBD plasma actuator , NACA0024 Airfoil , Separation point. , Flow Control , Induced flow
