Investigation of The Improvement of Airfoil Aerodynamic Performance by Using a Novel Mechanism to Adjust Different Cant Angles

This project is aiming to investigate the effect of variable winglet mechanism to adjust the cant angle towards overall wing aerodynamics performance in unmanned aerial vehicle $(U A V)$. The effect of cant angle and variable winglet mechanism is examined using computational method software ANSYS. The airfoil used is NACA 4415 and 2412 for the main wing and winglet respectively. The wing configuration consists of three different winglet cant angles and six angle of attack (AOA). The wing is tested with $k-\omega$ SST turbulence model along with SIMPLE Algorithm and Transient mode with velocity of M0.29.By implementing variable winglet mechanism, the overall lift-to-drag ratio $(L / D)$ is increased by up to 16.468% with reduction of drag coefficient by up to 14.267%. The addition of the novel mechanism also reduces the acoustic noise profile when compared to standard winglets.