The Effect Of Dielectric Barrier Discharge (DBD) Plasma Actuator On The Leading Edge Of An Airfoil

Suznan, Fazal Amsyar (2018) The Effect Of Dielectric Barrier Discharge (DBD) Plasma Actuator On The Leading Edge Of An Airfoil. Project Report. UTeM, Melaka, Malaysia. (Submitted)

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Abstract

Dielectric Barrier Discharge (DBD) plasma actuator has been found to be very useful in a wide area of applications. The various types and position of DBD plasma actuator can be applied for specific tasks. For instance, the used of DBD plasma actuator have been implemented on the surface of vehicles such as car and on the wing of aircraft. The DBD plasma actuator used in delay the flow separation occurs toward the surface of vehicles. By applying this method, a higher amount of lift force can be obtained at the critical angle of attack apply towards an airfoil and overcome the increasing drag force. Recently, the aerodynamics performances are frequently being studied for airflow control. The DBD plasma actuator has the ability to control airflow on wing profiles by maintaining the streamline of the boundary layer. This report attempts to define the principle and application of the DBD plasma actuator. DBD plasma actuator is introduced in the beginning a detailed review and designs is presented. Furthermore, for the outstanding findings for this thesis are, actuation case have better aerodynamics performance compared with baseline case and it achieved the functional application of DBD plasma actuator which are used to delay flow separation occurs on the surface of airfoil and prevent stall at higher angle of attack applied. Last but not least this thesis had fulfilled its objectives to investigate the effect of Dielectric Barrier Discharge (DBD) plasma actuator on the leading edge of airfoil and to compare the airfoil aerodynamic performance between base case and actuation case. The angle of attack used in the experiment range from 0° to 24°. The power supply used is 6 KV. The lift coefficient is increase as the angle of attack increases for both cases. The drag coefficient is decreases for actuation case. The experiment is conducted with velocity 15 m/s and 20 m/s. The finding of the study shows that by applying DBD plasma actuator, the value of lift coefficient of an airfoil shows an increment in range of 0.63% to 7.79% with different angle of attack for velocity of 15 m/s. However, the value of drag coefficient of an airfoil shows a declination in range of 3.25% to 100% with different angle of attack for velocity of 15 m/s. For velocity of 20 m/s, the value lift coefficient of an airfoil shows an increment in range of 0.51% to 3.3% and the value of drag coefficient shows a declination in range of 4.9% to 24.4% with different angle of attack. The aerodynamic performance can be improved by applying DBD plasma actuator as the lift coefficient is increase and drag coefficient is decrease based on the result of this study.

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