Wind Tunnel Testing of Mesh Electrodes Plasma Actuator

The paper presents the measurement methods and results of experimental investigations concerning the analysis of phenomena occurring on the surface of the wing with plasma actuator with two mesh electrodes and an impermeable dielectric placed on the surface of the wing model, with the profile SD 7003. Experimental tests with a plasma actuator were carried out at the State School of Higher Education in Chełm, in the Institute of Technical Sciences and Aviation. All experimental tests were carried out on for different configurations of the angle of attack of α = 15 degrees, and for the air velocity V = 5-15m/s, for the Reynolds number in a range of Re = 87500 - 262500.