The simulation of ice accretion on a wing or other surface is often required for aerodynamic evaluation. While there are commonly accepted practices for conducting this work, there are no established and validated guidelines. The purpose of this paper was to report the results of a study to establish a set of high-fidelity, full-scale, iced-airfoil aerodynamic performance data. These data were acquired as a part of a larger program with the goal of developing subscale simulation methods for ice accretion. Airfoil performance testing was carried out at the ONERA F1 pressurized wind tunnel using a 72inch (1828.8-mm) chord NACA 23012 airfoil over a Reynolds number range of 4.5x10⁶ to 16.0x10⁶ and a Mach number range of 0.10 to 0.28. Selected for testing were six, high-fidelity, ice-casting simulations classified by their aerodynamic effect. There was one horn shape, one spanwise-ridge shape, two streamwise shapes and two roughness shapes. The ice-shape simulations had a significant effect on the aerodynamic performance. The spanwiseridge shape resulted in a maximum lift coefficient of 0.56 compared to the clean value of 1.85 at Re = 15.9x10⁶ and M = 0.20. The two roughness and streamwise shapes yielded maximum lift values in the range of 1.09 to 1.28, which was a relatively small variation compared to the differences in the ice geometry. The stalling characteristics of the two roughness and one streamwise ice simulation maintained the abrupt leading-edge stall type of the clean NACA 23012 airfoil, despite the significant decrease in maximum lift. Changes in Reynolds and Mach number over the large range tested had little or no effect on the iced-airfoil performance. This result indicates that subscale aerodynamic simulation may be quite successful.