Aeroelastic Modeling and Drag Optimization of Flexible Wing Aircraft with Variable Camber Continuous Trailing Edge Flap

Abstract

This paper contains the development and optimization of an aeroelastic model of a flexible wing aircraft. The aircraft model is based on the NASA Generic Transport Model (GTM), with the wing structures of the model incorporating a novel aerodynamic control surface known as a Variable Camber Continuous Trailing Edge Flap (VCCTEF). The aeroelastic structural framework developed for the GTM model is implemented using finiteelement analysis. Aerodynamic modeling conducted using the vortex-lattice method is coupled with the structural framework through a geometry generation tool to form the static aeroelastic model. Constrained optimization using a surrogate function and sequence of approximations (SOA) optimization is conducted to tailor the wing twist for the aircraft’s design cruise flight condition. Further optimization is then conducted on the VCCTEF settings for drag reduction at off-design cruise flight conditions. The results demonstrate the potential of utilizing the novel control surface on aircraft for wing shaping control to improve aerodynamic efficiency.