In this study, an experiment was carried out to measure the performance of a delta wing with 65o 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.
Keywords: delta wing, plasma, actuator, lift, drag