Performance analysis of meta-morphing wing

Abstract

To adapt to a dynamic mission environment, morphing wings change their outer shape dramatically. As the airfoil thickness grows, the leading-edge radius advances, making the leading-edge smoother and allowing the laminar air to resist full swing separation at greater angles of attack. In this paper, the gear rod mechanism with rack and pinion is installed on the wings. In addition to the gear rod mechanism, corrugated shapes given at the trailing edge for elastic deformation. Flaps are used primarily on the leading and trailing edges of the wing to increase the lift coefficient and camber of the wing. A morphing mechanism would achieve leading and trailing edge deflection as well as airfoil thickness deflection at the same time. The morphing wing model is designed in CATIA V5 software with NACA 2415 airfoil coordinates. Designed model is analyzed in ANSYS workbench with various angles of attack such as -100, 00, 50 and 100 with velocity 50 m/s as boundary conditions. Aerodynamic efficiency CL/Cd is calculated for morphing wing and compared with convention wing. Fuel consumption is one of the performance parameters that might be developed using the morphing wing concept. This morphing wing is a brand-new mechanism concept that focuses only on the mechanism rather than the materials.