Numerical and experimental validation of an innovative anti-ice panel by means of computational fluid dynamics

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. The results achieved prove the model validity and accuracy. Subsequently, the ice accretion model has been implemented on a case study involving the Piaggio P180 airfoil. Moreover, two additional simulation models relative to the anti-ice and de-ice physic have been carried out. In the second part of this thesis work, the installation of the test bench, specially designed for the trabecular panels’ tests, has been presented. An additional CFD analysis has been performed in order to verify the proper flow alignment and structural resistance of the air duct. Finally, it has been submitted the first experimental campaign results proving the correct test bench functioning.