Abstract
Flow on an airfoil was investigated with plasma synthetic jet actuator. Plasma synthetic jet actuator is a flow control device which is composed of electrodes with A.C. signal, using electrohydrodynamic effect and induces a flow around the electrodes. From the characteristics of electrical device, plasma synthetic jet actuator has some important advantages; for example, miniaturization, maintenance free, and easy to control. From these characteristics, it is effective to apply flow control around an airfoil with plasma synthetic jet actuator. In this study, the behavior of the plasma synthetic jet actuator around an airfoil is observed by experiment. A NACA0012 airfoil with plasma synthetic jet actuator is set in the wind tunnel. The wake velocity behind air foil is measured with and without the actuator. Experimental result with the Delayed Feedback Control for the flow control system is shown in this paper. The results show good improvement for the plasma synthetic jet actuator to reduce drag in the high angle of attacks.
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