2020•The Proceedings of Mechanical Engineering Congress JapanOpen access
Effect of Wing Tip Vortex on Dynamic Lift Generation
Kazuki Ueda, Naoto Kato, Hiroaki HASEGAWA
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Abstract
The purpose of this study is to investigate the effect of wing tip vortex on unsteady fluid forces. In the present study, the angle of attack of the airfoil is impulsively changed from 0° to the angle set beyond the static stall angle by using a two-dimensional airfoil and a three-dimensional airfoil. When the airfoil is raised higher lift coefficient is attained than that of static lift coefficient. Lift coefficient gradually decreases asymptotically after attaining its maximum and reaches to the static one. The lift curve of three-dimensional airfoil is asymptotic more slowly than that of two-dimensional airfoil. The whole separation on the upper surface of the airfoil is suppressed by the wing tip vortex after the three-dimensional airfoil stops.
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