This paper describes experiments aimed at demonstrating the effectiveness of Pulsed Vortex Generator Jets in controlling separation on aircraft wings. The demonstration is accomplished by applying the jets to two relevant configurations and evaluating their effectiveness in a wind tunnel. The jet design and placement for both experiments was based on parametric studies described in a previous paper. In the first application, pulsed jets prevented separation over the wings on a three-dimensional lambda-wing fighter configuration at low speeds and high angles of attack. This experiment shows that the flow control method can enhance the lift, and hence the maneuverability, of advanced fighters in post-stall flight. The lambda-wing experiments also demonstrated that jets can be operated asymmetrically for lateral maneuvering control at high angles of attack. The second set of experiments tested higher speed ranges, applying jets to an airfoil section in a M = 0.3-0.5 flow. This configuration is relevant to subsonic cruise. The results show that Pulsed Vortex Generator Jets can increase lift and L/D, but they were less effective at supercritical speeds where separation is induced by hinge line shocks. In all cases, the jets increased lift over their effective range, while their drag effect was small.