This research starts with the development of decentralized, optimal, and adaptive controller design for a Variable Camber Continuous Trailing Edge Flap (VCCTEF) aircraft, the NASA Generic Transport Model (GTM), targeting the goal of minimizing the drag coefficient in cruise condition. To validate and generalize the developed controller design, a novel hybrid partial differential equation (PDE) model representing a flexible wing with rigid and flexible control surfaces was developed. To sense the shape of the flexible wing, the use of a novel sensor developed by NASA, called SansEC, was investigated. In this process, mathematical and artificial neural network (ANN) models of the sensor dynamics was developed with the help of results from experimental test data. It was concluded that the decentralized, optimal, and adaptive controller was successful in achieving the coefficient of drag minimization objective for the VCCTEF aircraft model as well as the hybrid PDE model. The SansEC sensor, with successful modeling, was deemed feasible for use as a sensor on aircraft wings to measure wing deflection. Additional research into the control design for the hybrid PDE model as well as real-world application of SansEC was determined to be necessary due to the limitations and scope of this research.