Static Aeroelasticity Considerations in Aerodynamic Adaptation of Wings for Low Drag

Abstract

This thesis presents a methodology to calculate the flap angles necessary to reproduce a desired lift distribution for an elastic wing with multiple trailing-edge flaps. The methodology presented builds upon the adaptive wing methodology for rigid wings developed by King and Gopalarathnam. Relevant equations from thin airfoil theory and beam theory are presented, and are then used to develop the solution procedure for the determination of flap angles for an elastic wing. Examples using an elliptic lift distribution are presented, and the effect of wing elasticity on the calculated flap angles and lift distributions is shown. Post-design analysis shows that the flap angles from the current method are successful in achieving an elliptical loading while accounting for using torsional deformations. The methodology is verified by comparing the twist predicted by the methodology to the twist predicted by a finite element analysis. Finally, an example demonstrating how the methodology handles flap effectiveness and flap reversal is provided.