Flow control and lift/drag change analysis with movable wing tip design

Aviation studies are increasing in importance in the field of military and civil transportation. In particular, the expectation of higher aerodynamic performance of aircraft is increasing. In this study, a Clark-Y wing geometry, which is frequently used in practice, was first verified. Then, 11.25 cm sections were designed at the wing tips that could be moved with a servo motor. By keeping the angle of attack of the flight constant at 5 degrees, the effect of winglet angle change on lift and drag forces was examined. The study results showed that the lift/drag value decreased if the wing tip attack angle was increased above 5 degrees. However, since the wing angle of attack remained constant, the aircraft survived the stall effect and there was no significant increase in drag force. Although the moving wing attachment and high angles of attack reduce the lift/drag value, it is highly usable in applications requiring high lift.