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This paper describes a physics-based icing tool for aircraft engines, which have small components compared to the wing geometry of an aircraft. The tool consists of an icing code, viscous CFD software and mesh generator to build ice shapes incrementally to form the final shape. This multi-layered process was developed to predict ice shapes in components with high-pressure gradient flows as found inside engine flow passages. Good agreement was found between experimental and predicted ice shapes for engine inlet guide vanes and different wing geometries.

The present paper showcases the predicting ability of an in-house 2D/ Quasi-3D steady state Ice Crystal Accretion Tool (ICAT) applicable for both heated and un-heated surfaces. The previously existing code for unheated surfaces, has been extended to heated scenarios with the inclusion of: 1) coupling with solid conduction model 2) inclusion of advanced models for crystal melting, water film modeling, sticking and erosion. The results obtained from ICAT are verified against the experimental results of heated NACA0012 airfoil, conducted in the icing wind tunnel of TU Braunschweig as part of MUSIC-haic project. ICAT predictions are found to be well in agreement with the ICI physics, which is proven with the various parameters addressed in this paper, such as tunnel temperature, ice crystal temperature, inlet melt ratio, heating power, etc.