The ice ridge will reduce the aerodynamic performance of the wing, which is an important factor endangering flight safety The air flow field was obtained by solving the N-S equations using the structured mesh and the central finite volume method. The Lagrange method was used to obtain the impingement characteristics of the water droplets. The leading edge icing of the NACA 0012 airfoil was numerically simulated based on the Messinger icing thermodynamic model. The ice shapes are in good agreement with the experimental data, which verifies the accuracy and feasibility of the calculation method. Based on this, the anti-icing zone is set on the NACA 0012 airfoil and the anti-icing thermal load is considered. The formation of ice ridges under large water droplet conditions was simulated. The effect of ambient temperature, liquid water content, and thermal load on the formation of ice ridges was obtained. The results show that in the case of large water droplets, the increase in ambient temperature makes the range of ice ridges increase and the height decrease; the increase of liquid water content makes the range of ice ridges increase and the height increase; the increase of anti-icing thermal load can make both the range and height of ice ridge decrease. The study of its influence law has a reference value for the design of anti-icing device. In the case of large water droplets, NSDBD can make the ice ridge formed under low liquid water content disappear and push back the formation position of ice ridge under high liquid water content.