Abstract
Using a dielectric barrier discharge plasma actuator (DBD-PA), an active control system for flow separation around the MEL001 airfoil was attempted successfully at Re = 3.2×10^4. DBD-PA consists of top and bottom electrodes and a dielectric layer placed between the electrodes. Tangential jet velocities reach their maximum (V_<j-max>) in the range of 0.12 ≤ V_<j-max> ≤ 1.05 m/s, when bipolar sinusoidal wave voltages are applied, ±2.0, ±2.25, ±2.5, ±2.75, ±3.0 kV at 50 kHz. A series of experiments was carried out in the open-circuit blower type wind tunnel with 200mm×200mm×500mm test section under free stream velocity of U_∞ = 3.2 m/s. A DBD plasma actuator was installed on the MEL001 airfoil (chord length: L = 50 mm, wingspan: W = 200 mm). The wing was set in the test section with angles of attack (a) at a = 8.2 and 12.0 degrees. The effective jet velocities and power consumptions required to suppress flow separation were estimated by the velocity distributions around the airfoil and the current and voltage data so far accumulated on DBD-PA.
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