Abstract
Active control of flow near the trailing edge on a NACA0015 airfoil has been conducted by a dielectric barrier discharge plasma actuators (DBD-PA). The edge of exposed electrode is located at x/c = 0.9 on the pressure surface of NACA0015 and tangential jet, which the maximum velocity normalized by free stream velocity is u_<max>/U_∞ = 0.09, is induced under the flow condition of Re = 3.3×10^4 by applying peak to peak voltage of 5.0 kV at 8.7 kHz toward the upstream direction. In order to evaluate flow control effects, lift and drag were measured by a force balance system. NACA0015 airfoil with Gurney flap were also tested to make a comparison between the aerodynamic performances of the normal NACA0015 with and without flow control. It was found that the lift under flow control and with Gurney flap are enhanced in the range of angle of attack -10° ≤ α ≤ 10°. In addition, velocity distributions were measured by a PIV system and confirmed the differences of those distributions near the trailing edge between NACA0015 without Gurney flap under flow control and with Gurney flap.
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