Turbomachinery

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Separation of flow is typically an undesirable phenomenon in engineering practices because it entails large energy losses in fluid machinery and stall on airfoils. Therefore, boundary layer control has been used widely in aerodynamic applications to inhibit flow separation and one of the effective technique of the active boundary layer control is a synthetic jet actuator. In the present study, the active separation control system using synthetic jets is proposed and is practically applied to the stall control of the NACA0012 airfoil in a wind tunnel test. In our proposed system, the flow conditions (stalled or unstalled) can be judged by using pressure difference between two static pressure holes on the airfoil upper surface alone. The proposed system can be operated prior to the onset of stall, and therefore, a separation control is always attained with no stall for flow fields produced by continuous change in the angle of attack tested in this study.

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