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《High Voltage Engineering》 2014-01
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Experimental Investigation of Airfoil Flow Separation Control by Dielectric Barrier Discharge Plasma Actuator

YANG Bo;SUN Min;BAI Mindi;Department of Physics, Dalian Maritime University;  
To improve plasma aerodynamic actuator, through smoke wire visualization experiments, we investigated the performance of a dielectric barrier discharge(DBD) plasma actuator on controlling the plasma flow separation of NACA0015 airfoil at different free-stream velocities and different angles of attack. The actuator uses α-Al2 O3 as its dielectric material. The experimental results show that plasma actuation can effectively suppress the flow separation at low free-stream velocities and high attack angles. When the free-stream velocity is 35 m/s, plasma actuation increases the stall angle by 1.5°, while the suppressing effect of plasma flow separation decreases with the increase of the angle of attack. When the angle of attack is 20.5° and the free-stream velocity within 30~44 m/s, the plasma flow control shows a tendency of "weakening-enhancing-weakening" with the increase of free-stream velocity. The location of the plasma actuator on the airfoil is found to be crucial for suppressing flow separation; better effect is obtained when the plasma actuator is close to the separation point. The plasma is able to suppress the separated flow at the free-stream velocity of 60 m/s, with an increase in lift force by 31.1% and a decrease in drag force by 27.8%.
【Fund】: 国家自然科学基金(60801010)~~
【CateGory Index】: O53
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