Advanced measurements of a tip clearance flow are carried out in the large subsonic anechoic wind tunnel of the LMFA in Lyon. The experimental set-up is obtained by placing the airfoil between two plates into the potential core of a turbulent rectangular jet, the upper plate being the hub and the lower the casing. The jet that exits a converging nozzle has a 450 mm cross-stream width and a 200 mm height in the span-wise direction. An h=10 mm gap is maintained between the blade and the casing plate. The incoming free stream turbulence u’/U0 is 0.5%, and the flat plate boundary layer half a chord upstream of the airfoil leading edge is about 8 mm thick. Except for the thickness being halved, the configuration is the same as the one discussed by Jacob et al.1, I.J.A, 9(3), (2010) , and Camussi et al.2, J.F.M., 660, (2010): a M ~ 0.2 and Rec ~ 950000 jet flow past a NACA5510 airfoil with 15° angle of attack. Measurements are carried out in the region of the Tip Leakage Vortex (TLV) in order to characterise its unsteady velocity. Both 2D–2 Component and stereo Time Resolved PIV techniques are successfully applied in order to provide an insight into the low frequency content of the velocity field, that are compared to LDV measurements. This experiment corresponds to a novel type of configuration that has only been studied by Jacob et al. Moreover, the TR-PIV and specifically the stereo-TR PIV are quite new techniques that have not often been applied to such complex configurations at such high speeds. The benefits of the time resolution are promising for the understanding of such broadband noise sources. Among the findings, there is a low frequency oscillation of the TLV, whose mechanism is yet unclear but which does not seem to radiate into the far field. Additionally, a hump at medium and high frequencies (0.7 – 7 kHz) is found in the far field. It can also be related to time decay double space-time correlations.