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In this study, an experiment was carried out to measure the performance of a delta wing with 65 o swept angle. The measurement of lift and drag on the delta wing with and without plasma actuator was the main focus of this research. Multi-DBD plasma actuator was implemented on top of the wing. The experiment was conducted in a wind tunnel with a free stream velocity of 5.74 m/s or at Reynolds number of 83000. The performance of the wing was positively affected by the use of plasma actuator, indicated by the increasing lift coefficient and the decreasing drag coefficient, as maximum increase of 0.078 in lift coefficient and 0.053 decrease in drag coefficient were obtained.

This paper shows experimental results for velocity measurement in the boundary layer with the use of a flat plate model. The flat plate model is disrupted with a wire trip and the effect of the plasma actuator to alter the flow in the boundary layer is then observed. The purpose of this research is to characterize the performance of the plasma actuator in a noflow condition and with the use of a 2 m/s flow and also to theoretically analyze the performance of actuator in the boundary layer namely, displacement thickness, momentum thickness, and energy thickness. This is all done to acquire a deeper understanding of the capabilities of plasma actuator as one of the alternative active flow control equipment and to increase the effect of aerodynamic drag reduction. One of the ways to decrease the aerodynamic drag is to manipulate the flow to have a low boundary layer thickness value in order to prevent an adverse pressure gradient from happening, which then may lead to the formation of a flow separation. From experimental results, it is known that plasma actuator could decrease the thickness of the boundary layer by 9 mm.

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