A mathematical model for simulation of icing dedicated to simulation of ice accretion and its effects on aircraft
aerodynamic characteristics in conditions of rime icing is presented. Pure rime icing occurs at lower temperatures
than glaze icing and results in higher roughness of the surface of deposited ice. The model accounts for increased
surface roughness, in terms of equivalent sand grain roughness, caused by deposited rime ice, which influences
generation and dispersion of heat in the boundary layer. Increase of surface roughness is determined by analytical
models created upon experimental data obtained in icing wind tunnels. Increased generation of heat is a result
of increased tangential stress on the surface and is quantified in the temperature recovery factor determined
numerically by a CFD solver. Effects of surface roughness on the intensity of forced convection are quantified
by application of Colburn analogy between heat and momentum transfer in the boundary layer, which allows
assessment of heat transfer coefficient for known friction coefficient, determined by CFD. The computational method
includes determination of the surface distribution of mass of captured water in icing conditions. The model of freezing
of captured water accounts for generation of heat due to latent heat of captured water droplets, temperature recovery
in boundary layer and kinetic energy of captured droplets. The sinks of heat include forced convection, heating
of super cooled droplets, conduction of heat through the ice layer and sublimation. The mathematical model
is implemented as user-defined function module in ANSYS Fluent solver. The results include effects of deposited ice,
including increased surface roughness on aerodynamic characteristics of an airfoil.
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