This paper presents an experimental investigation of the effect of the dielectric barrier discharge plasma actuators on the leading-edge vortex flow control over a delta wing with a 75 deg swept angle. The Reynolds number based on the delta wing chord is 50,000. The smoke flow visualization and particle image velocimetry experiments in the wind tunnel indicate that the asymmetric control caused by the dielectric barrier discharge plasma actuator can significantly affect the global flow structure over the delta wing: the leading-edge vortex breakdown position on the same side of the actuator is advanced, whereas vortex breakdown on the other side is delayed. This phenomenon is observed for the first time and is only observed in the current full-span delta wing experiment, significantly different from the result of the semispan experiment. The force measurement result shows that the asymmetric control has a limited contribution to lift generation but can induce a relatively large roll moment.
ASJC Scopus subject areas
- Aerospace Engineering