Flowfield measurements were carried out on the upper surface of a GLC-305 airfoil configured with glaze and rime ice-shape simulations. The mean and root-mean-square fluctuation of the streamwise velocity were measured using a split-hot-film probe at several chordwise locations. These data were taken at three different angles of attack preceding stall for each iced-airfoil configuration at Reynolds numbers of 3.5 x 10⁶ and 6.0 x 10⁶ with Mach numbers of 0.12 and 0.21. The velocity measurements confirmed the presence of a large separation bubble downstream of the ice shapes. The separation bubbles for the glaze ice configuration were much larger than those for the rime ice case,resulting from the differences in the ice horn geometry. Other than the differences in size, the integral boundary-layer characteristics were very similar. Changes in Reynolds number did not significantly affect the separation bubble characteristics. However, a larger Mach number did result in a slightly larger separation bubble for the glaze ice case at a = 6 deg. The root-mean-square velocity distributions had peak values in the separated shear layer, downstream of transition, that compared well with previous work.