Numerical Investigation of Continuous Morphing Trailing-edge Wing for Improving the Aerodynamic Characteristics

Abstract

Morphing technology is one of the most effective ways to increase aircraft flight efficiency. Traditional morphing based on control surfaces is mature and widely utilised on aircrafts, but it is insufficiently effective across the entire flight envelope. This study explores the effectiveness of morphing technology in enhancing aircraft wing performance, aiming to develop a continuously morphing trailing-edge wing for superior aerodynamic efficiency. Using numerical simulations, various morphing wing profiles, including traditional flap morphing wings are evaluated. The deflection angles are varied from 0° to 20° and the aerofoils are studied at varied angle of attacks ±15°. Findings reveal that continuous morphing trailing-edge wing offers substantial advantages over conventional designs by exhibiting improved lift coefficients (7.5-10%) at high deflection angles, thereby enhancing manoeuvrability and flight control. Moreover, it demonstrates superior aerodynamic characteristics at low angles of attack (AoA), leading to enhanced fuel economy. The drag reduction (5-10%) during morphing manoeuvres minimizes performance losses, contributing to overall aerodynamic efficiency. Finally, the comparative analysis underscores the superiority of the continuously morphing trailing-edge wing, showcasing its ability to delay flow separation and control pressure distribution, thereby enhancing aerodynamic capabilities.