Using a surface flow visualization approach, this movie depicts the surface flow pattern across an airfoil wing. It demonstrates the impact of sweeping jet actuator spacing at a fixed actuator position (corresponding to the model's 12% chord). Additionally, flow reversal is seen close to the trailing edge of the wing. Furthermore, displays how actuation at pre-stall, near-stall, and post-stall angle of attacks affects the flow separation. Increasing the momentum of fluid inside the boundary layer using oscillators delays flow separation and the consequent rise in lift with increasing flow rate.