Experiments are performed on a 82.5 • sweep flat-plate delta wing combined with a dorsal fin of height 0.6 of the wing semi-span at Reynolds number based on the wing root chord of 3.32×10 5 , in which a pair of small and short dielectric barrier discharge plasma actuators are employed at the wing leading edge near the apex of the wing to effect flow control. Measured pressure distributions over the model are investigated. Lateral flow control is achieved at angle of attack of 30 • by the plasma actuators. Flow induced by the leading-edge plasma actuator in still air is also studied. Ideals for further work are suggested.