Effect Of DBD Plasma Actuator At The Middle Span Of Airfoil

Qasem Al-Areqi, Qasem Ahmed (2018) Effect Of DBD Plasma Actuator At The Middle Span Of Airfoil. Project Report. UTeM, Melaka, Malaysia. (Submitted)

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Abstract

The lift force is perpendicular to the line of the airfoil such as wing of aircraft, is generated when an aircraft moves through the air. The pilot controls the movement of the aircraft by flaps and slates. When the plane rises up, increase the angle of attack of airfoil and this lead to stall, the flow molecules lose momentum and decrease the lift force. In this study, the dielectric barrier discharge (DBD) plasma actuator is used to improve the aerodynamic performance of airfoil. The DBD plasma actuator is located at the middle of airfoil. Driven by voltage AC 6 kV and frequency 8 kHz waveform sinusoidal actuator are composed of two copper-tape electrodes, each 50 μm thick and 5 mm wide and Kapton film have 100 μm thickness act as dielectric which separated between the electrodes and arranged in an asymmetric fashion was tested and developed on NACA 0015 airfoil. The result of the experiment showed is successful by positive value of the lift coefficient the airfoil, where enhancement ranged between angle of attack 0°−14°. However, at high angle of attack, the result showed in negative value it was not expected due to the power was not sufficient to improve the lift coefficient of the airfoil. Furthermore, is needing to increase the voltage supply and other equipment to improve the actuator in refining the aerodynamic performance of the airfoil.

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