Abstract
CFD analysis of the flow around the wing using closed-loop feedback control was investigated with plasma synthetic jet actuator. Plasma synthetic jet actuator is a flow control device which is composed of the electrodes with A.C. signal, using electro hydrodynamic (EHD) 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 wings. With this actuator, the flow around the wing controlled by the delayed feedback control (DFC) has shown high effect to reduce the drag and separation in the wind tunnel tests. In this study, the CFD analysis is held to see the effect of the DFC to the flow around the wing including precise flow stream, which is difficult to measure in actual wind tunnel testing. The conditions of CFD is set as equal to that of the low wind tunnel testing using a NACA 0012 aerofoil. The actuator actuates the flow according to the body force calculated computationally by the induced voltage between the isolated electrodes. The CFD analysis shows that the DFC reduces the drag and forces the position of the flow separation to down stream. These results show good agreement with that of the wind tunnel tests.
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