The separation bubble on a NACA 0012 airfoil with two- and three-dimensional, simulated, leading-edge, glaze-ice accretions was investigated using Particle Image Velocimetry (PIV). Chordwise PIV measurements, or those along the separation bubble cross-section, were obtained at a Reynolds number of 0.9x10⁶, Mach number of 0.20, and between 0-deg and 5-deg angle-of-attack. Surface oil-flow visualization indicated increasing separation bubble length with airfoil angle-of-attack. Shorter separation bubble length at constant angle-of-attack and spanwise flow inside the separation bubble were also observed behind the three-dimensional ice simulation. Time-averaged PIV results revealed a primary recirculation with clockwise rotation defined by a shear layer and a smaller, secondary recirculation with counter-clockwise rotation directly downstream of the point of separation, both consistent with backward-facing-step-type flowfields. Mean and RMS velocity component contours highlighted these features and surface-normal profiles were extracted and compared to identify similarities and differences between the ice accretion flowfields which might explain the varying separation bubble lengths and spanwise instability observed in the flow visualization.