Simulation of rime icing and its effects on aerodynamic characteristics of an airfoil

• Autorzy: Sznajder J.

Identyfikatory

DOI

10.5604/01.3001.0012.4362

• Języki publikacji: EN

Abstrakty

EN

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.

Słowa kluczowe

EN

computational fluid dynamics; aerodynamics; two-phase flow; simulation of ice accretion; heat exchange; aircraft engineering; transport; vehicle

• Wydawca: Łukasiewicz Research Network - Institute of Aviation ; European Science Society of Powertrain and Transport KONES Poland ; Wydawnictwo Instytutu Technicznego Wojsk Lotniczych
• Czasopismo: Journal of KONES
• Rocznik: 2018
• Tom: Vol. 25, No. 3
• Strony: 437--443
• Opis fizyczny: Bibliogr. 7 poz., rys.

Twórcy

autor

Sznajder J.

• Institute of Aviation, Department of Aerodynamics Krakowska Av. 110/114, 02-256 Warsaw, Poland tel.: [phone] ext. 492, fax: [phone]

Bibliografia

• [1] Shin, J., Bond, T. H., Experimental and computational ice shapes and resulting drag increase for a NACA 0012 airfoil, NASA Technical Memorandum 105743, 1992
• [2] Versteeg, H. K., Malalasekera, W., An introduction to computational fluid dynamics, Pearson Education Limited, 1995, 2007.
• [3] Nikuradse, J., Laws of flow in rough pipes, National Advisory Committee for Aeronautics, Technical Memorandum 1292, 1950.
• [4] ANSYS Documentation, available with software and online at https://ansyshelp.ansys.com, ANSYS, v.18.
• [5] Myers, T., Extension to the Messinger model for aircraft icing, AIAA Journal, Vol. 39, No. 2, 2001.
• [6] Sznajder, J., Determination of water collection on two- and three-dimensional aerodynamic surfaces in external two-phase flow in atmospheric conditions, Journal of KONES Powertrain and Transport, Vol. 23, No. 1, pp. 369-376, 2016.
• [7] Sznajder, J., Sieradzki, A., Stalewski, W., Determination of ice deposit shape and ice accretion rate on airfoil in atmospheric icing conditions and its effects on airfoil charac-teristics, Journal of KONES Powertrain and Transport, Vol. 24, No. 2, pp. 271-278, 2017.

Uwagi

Opracowanie rekordu w ramach umowy 509/P-DUN/2018 ze środków MNiSW przeznaczonych na działalność upowszechniającą naukę (2018).