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Journal of Applied Fluid Mechanics، جلد ۹، شماره ۲، صفحات ۸۷۷-۸۸۸
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عنوان انگلیسی Experimental Investigation of Separation Control on a NACA0024 Airfoil using Stationary and Non-Stationary AC-Dielectric Barrier Discharge Plasma Actuator
چکیده انگلیسی مقاله 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.
کلیدواژه‌های انگلیسی مقاله Flow control, Induced flow, NACA0024 Airfoil, DBD plasma actuator, Separation point
نویسندگان مقاله 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 92697-3100, 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 92612, USA

نشانی اینترنتی https://www.jafmonline.net/article_1668_a4a36c80fbaaaf308a061a5a3d0bd0ed.pdf
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