An experimental investigation was conducted to determine the effect of simulated-spanwise-ice shapes on airfoil aerodynamics. The simulated ice shapes were tested on the NACA 23012 and the NLF 0414 airfoils at Re = 1.8 million. The ice shapes produced very different results on the two airfoils. The effects of the simulated ice shapes were much more severe on the NACA 23012, with a C_l,max as low as 0.25 for the ice shape with a height to chord ratio of 0.0139. The lowest C_l,max measured for the NLF 0414 with same ice shape was 0.68. The effect of the simulated ice shape on the flap hinge moment was much more severe on the NACA 23012 than on the NLF 0414. The NACA 23012 effects were more severe due to the large adverse pressure gradients at the ice-shape location. Various simulated ice shape size and geometries were investigated on the NACA 23012. The aerodynamic penalties (in C_l, C_d, C_m, and C_h) became more severe as the height to chord ratio of the simulated ice shape was increased from 0.0056 to 0.0139. The variations in the simulated ice shape geometry also had measurable effects on the airfoil aerodynamics.