Mechanism and Performance Analysis of Morphing Wing

Abstract

Morphing wing concept is introduced to analyses wings aerodynamic performance the through warping mechanism. Thread rod mechanism is installed at the trailing edge of the wing to warp. Relative displacement between upper and lower skin of wing leads to have twisted wing. This new concept is applied at the demonstration wing which was built based on NACA 23012 airfoil section with a span of 0.580m and a chord length of 0.235m. Demonstrated model was tested using wind tunnel and analysis software. In general, it was demonstrated at lower AOA and the tests showed that warping could change the lift force in optimized manner. This study proved that a morphing wing can have optimum L/D ratio to minimize the fuel consumption of an aircraft and to ensure that the lift-to-drag ratio remains constant at various flight conditions.