In order to develop an innovative trabecular anti-ice system, this thesis work has investigated in detail the ice accretion phenomenon, implementing specific Computational Fluid Dynamic (CFD) models. After a general overview on the current de-ice/anti-ice systems, an extensive literature search relative to the mathematical icing models has been carried out. With the purpose of studying the best meshing strategy, a detailed design of experiment has been implemented. The work has been focused on the ice accretion simulation on an aircraft wing, by using the CFD software STAR CCM+. Different icing conditions have been evaluated and the model has subsequently been validated by mean of the experimental icing tests conducted at the NASA Icing Research Tunnel.