High lift multielement airfoils, such as those used on large transport aircraft during takeoff and landing, can generate strong adverse pressure gradients that, while the surface flow is attached, can cause off-thesurface separation in the wake, so called, wake bursting. The sudden expansion and thickening of the separatedwakes has been shown to decrease lift and increase drag. Wake bursting was experimentally studied over athree-element high lift airfoil, and unsteady velocity measurements were taken with a split film probe. The tests were performed in the University of Illinois low-speed low-turbulence subsonic wind tunnel on a multielement airfoil having a chord length of 1.35 ft (0.411 m) and a model span of 2.8 ft (0.85 m). Results for a Reynolds number of 1e6 indicate that wake bursting was observed for the wake of the main element and the first flap. A methodology was developed to numerically define the core of each wake both upstream and downstream of the burst point. Data show that the local flowfield angle in the wake core does not significantly change relative to the flowfield outside the wake core. Unsteady results indicate that the velocity fluctuations within the burstwake region are dominated by turbulence in the shear layers between the wakes with less turbulence observed in the wake cores. These turbulent fluctuations were largest in the shear layers and were observed to spread into the wake cores.