Experimental study on wing tip vortex near field

An experimental study of the wing tip vortex is performed on a rectangular wing with NACA0015 airfoil and both squared and rounded tip. The tests are performed at Reynolds 5 105 and 1 106 while the angle of attack varies between 4 and 15 . The main measurement technique is the Stereo Particle Image Velocimetry based on LaVision system. Additional data are obtained from surface ow visualizations and pressure measurements. The most salient topics concerning the wing tip vortex near eld have been dealt with, such as axial velocity behavior at the vortex centre, secondary vor- tices, and aperiodicity correction methods. All the experiments were performed at the Aerospace Engineering Depart- ment of The University of Glasgow collaborating in a PhD research program.