EXPERIMENTAL ANALYSIS OF THE EFFECT OF PLASMA ACTUATOR ON FLOW CONTROL ON NACA 4412 AIRFOILGokcen Jurnal, Cem Kolbakir, Ahmet Selim Durna and Burak Karadag In this study, the effect of a DBD plasma actuator on controlling the flow over a 3D-printed NACA 4412 airfoil was experimentally examined. Firstly, plasma actuator installation was investigated on the flat plate for different dielectric layer thickness and electrode length. Secondly, smoke visualization experiments were performed with the printed airfoil for 8 different spanwise electrode configurations in a small-scale wind tunnel at a Reynolds number of 35000 to determine the optimum configuration. It was found that the plasma actuation effect is higher for the configurations that have multiple electrodes spread on the airfoil surface than the single electrode configurations. This effect reduces flow separation and delays the stall of the airfoil, which may be related to the boundary layer thickness, and the effect becomes more significant as the angle of attack decreases. |