Computational Simulation of Glaze Ice Accretion on a Rotorcraft Engine Intake in Large Supercooled Droplet Icing Conditions

Abstract

This study presents a three-dimensional computational model to compute glaze ice accretion on complex configurations. A unified analysis system of clean air, droplet impingement, and ice accretion?all of which are based on a single unstructured upwind finite volume framework? was used in the ice accretion simulation. During the process, supercooled large droplet dynamics was also incorporated into the unified computational framework when computing the droplet impingement and the collection efficiency. The droplet impingement results predicted by current models were shown in close agreement with the other results. Moreover, the glaze ice accretion results were found in close agreement with icing wind tunnel data. Finally, we apply the unified numerical solver to investigate glaze ice accretion on a rotorcraft engine intake in supercooled large droplet icing conditions. ? 2022, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.