<p>In this paper, a novel model is presented for the analysis of flutter wings of aircraft with airfoil shape cross-section of the wing. In addition, two strong nonlinear controllers including feedback linearization (FL) and sliding modes (SMC) are employed to control the system. Piezoelectric is employed here to control the wing in the presence of aerodynamic disturbances. The flutter of aircraft wings can cause unwanted deviations in the aircraft maneuver as soon as its initiation which prevents the pilot from performing the aircraft's navigation and it cannot be ignored for a long time period without control since its related amplitude increases quickly and may even result in the failure of mechanical structures. Precise modeling is the first step in efficient control of the flutter. Thus, here the real cross section of the wing which has an airfoil shape is considered to model the beam vibrations. Because flutter is a self-excited vibration, modeling the aeroelasticity dynamics is also extremely significant in controlling the flutter, and thus, its dynamics are coupled here to the model. Finally, FL and SMC are implemented in the system and their results are compared. To meet this goal, a nonlinear closed-loop controller has been developed for wing vibration. Afterward, to extend the controlling strategy, FL and SMC formulations are implemented on the flutter dynamics. The accuracy of modeling and efficiency of the proposed model and controllers are verified and investigated with the aid of some simulation scenarios. It is shown that the proposed model provides a more realistic plant for flutter and the proposed controller can successfully stabilize the vibrating disturbance through the wing toward minimizing the aircraft deviation during its maneuver process.</p>