Reduction of aerofoil self-noise by surface plasma technique

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In the aerospace industry, great emphasis is always placed on the lifting components to achieve high-lift, low-drag and low-noise performances. This proposal concerns an 18-month experimental study into the application of surface plasma actuators as an active boundary layer and wake control technique with the aim of reducing the drag and Trailing Edge self-noise of aerofoil. Two configurations will be investigated: (1) an aerofoil with blunt trailing edge - which characteristically combines a superior lift performance with high drag and significant tone noise radiation; (2) an aerofoil with a sharp trailing edge - which typically produces broadband self-noise in high Reynolds number flow. The main technology under investigation here is the relatively new, though rapidly expanding, surface plasma actuators. The usage of surface plasma actuators for flow control is very attractive for industrial applications because this technique is highly energy efficient, has a fast response, a simple structure, can be used for both steady and unsteady actuations and creates no profile drag when not in operation. The proposed research aims to simultaneously optimise the aerodynamical and aeroacoustical performances of aerofoil with blunt as well as sharp trailing edges. The expected outcome of this research is an extensive validation of the effectiveness of surface plasma actuator as a relatively novel technique for the reduction of drag and noise generated by aircraft components such as the turbofan engine and airframe. The outcome of this research is also transferable to the wind turbine industry and fan-based home appliance sector.