Host: The Japan Society of Mechanical Engineers
Name : [in Japanese]
Date : November 07, 2019 - November 08, 2019
The wing-tip vortex is closely related to the induced drag of airplane, and its suppression is desired to improve flight efficiency. In the present study, the decay of the wing-tip vortex is enhanced by introducing wing-tip vibration. A vibrating wing-tip is attached to a NACA0012 half wing model. The stereo PIV measurements at z/c = 4 have been performed to evaluate the velocity distribution of the vortex. The vibration frequency, f, and the angle of attack of the wing, α are taken as parameters for the present experiment. The effect of the wing-tip vibration is observed both in the axial and in-plane velocity distributions. For the stationary case at larger angle of attack, α = 7 deg and 10 deg, the tangential velocity of the vortex exhibits a distinct peak in its radial profile. This peak disappears with the wing vibration indicating that the core of the wing tip vortex is weakened by the vibration. It is confirmed that the vibration of the wing-tip exerts significant impact on the development of the wing-tip vortex.
