Experimental Investigation of Aerodynamics Performance of Biomimicry Morphing Wing of NACA0012 Airfoil at Trailing Edge Deflections

Morphing wings can significantly improve aerodynamic efficiency, drag reduction, noise reduction, adaptive performance, reduce fuel consumption and increase flight range. This study aims to morph the NACA0012 airfoil trailing and leading edges using pneumatics and electronics to different angles. The pneumatics cylinder of 16mm bore 80mm stroke length with double electronic triggered 5/3-way solenoid valve, is used to control the trailing edge deflection angle of 0°, 5°, 10°, 15°, 20° and 25° morphing along with high torque standard servo motors at the tip of trailing edge to give additional morphing ability for reliability of the wings in case of safe operation during failure of pneumatics. The deflected morphing is placed in the low-speed suction types wind tunnel test section to find out the force measurement under different freestream velocities such as 5m/s, 10m/s,15m/s, 20m/s and various angle of 0°, 4°, 8°, 12° and 16°. As the trailing edge is deflecting the chord associated with it can be changed making the wing adaptive to all flight conditions. The main objective of this study is to improve the aerodynamics performance using biomimicry morphing wing with trailing edge deflection, analyse lift and drag of morphing wing at all possible deflection angles and different freestream conditions using low speed wind tunnel.