Control response of continuous trailing edge morphing wings

Résumé fourni par la source

In this research, the morphing wing geometries are studied parametrically to identify the aerodynamic characteristics at various flight conditions. The morphing wing presented considers a NACA 0012 airfoil with a rigid portion at the leading edge and a continuously conforming trailing edge flap. Following the authors' previous study, an elliptical curve was used as the morphing model for the spanwise trailing edge deflection. Control deflection for the trailing edge, hinge location, Reynolds number, and angle of attack were parameterized to investigate trends. This research was conducted numerically through Computational Fluid Dynamics (CFD) simulations. The CFD simulations are performed using the three- dimensional (3D) Reynolds-Average Navier-Stokes (RANS) equations with the k – ω Shear Stress Transport (SST) turbulence model. The results showed that a higher Reynolds number leads to better aerodynamic performance while the control deflection and hinge location needs to be optimized for a given flight condition. The results also indicated that the morphing wing shape optimization should start from lower values of control deflection and hinge location as an initial design approach. The study demonstrates that morphing wings can achieve significant aerodynamic performance gains through active actuation of hinge point location and control deflection to suit the flight regimes encountered through a mission profile.

Ce résumé expose les affirmations des auteurs. BNTIC ne l’interprète pas comme une validation indépendante des résultats.