An experimental investigation on active control of aeroelastic aircraft wing structures using piezoelectric actuators and sensors is presented. To this end, wind tunnel and remotely piloted vehicle wing models were designed, fabricated, installed, and tested. Computational structural and aerodynamic wing models were created, in order to determine the wing natural frequencies and modal shapes, and to predict the flutter speed. A digital controller was designed and implemented. Open and closedloop vibration and flutter tests were conducted in the wind tunnel and in flight, with excellent correlation achieved with computational predictions. Two different active wing concepts were analyzed:​ the first model consists of a wing with piezoelectric actuators attached to the wing skin, and the second wing model has piezoelectric actuators mounted in the main spar. The experimental results obtained have shown that the adaptive wing response had improvements in almost all the RPV flying conditions compared to the corresponding passive wing vibration, for both the active skin and the active spar wing concepts. Also, it was demonstrated that the flutter speed of the active wings increased compared to the corresponding passive wing