Determination of ice deposit shape and ice accretion rate on airfoil in atmospheric icing conditions and its effects on airfoil characteristics

• Autorzy: Sznajder J. , Sieradzki A. , Stalewski W.

Identyfikatory

DOI

10.5604/01.3001.0010.2946

• Języki publikacji: EN

Abstrakty

EN

Simulations of ice accretion on airfoil in icing conditions were conducted using ice accretion model implemented by authors in ANSYS FLUENT CFD solver. The computational model includes several sub-models intended for simulations of two-phase flow, determination of zones of water droplets impinging on the investigated surface, flow of water in a thin film on airfoil surface and heat balance in air-water-ice contact zone. The method operates in an iterative loop, which enables determination of effects of gradual deformation of aircraft surface on airflow over the surface, which has impact on distribution of collected water, flow of water film over the surface and local freezing rates. The implementation of the method in CFD solver made it necessary to complement the mathematical model of determination of local rates of deformation of aircraft surface with modification of computational mesh around the surface, which must conform, to the deformed surface. Results of simulated ice accretion on NACA 0012 airfoil were compared with results of experiment conducted in icing wind tunnel for a 420 s long process of ice accretion in steady-flow, steady angle-of-attack conditions. Close agreement of values and location of maximum ice thickness obtained in experiment and in the flow, simulations can be observed. For the airfoil deformed with ice, contour determination of its aerodynamic characteristics at several other angles of attack was conducted proving dramatic degradation of its aerodynamic characteristics due to ice deformation.

Słowa kluczowe

EN

aerodynamics; two-phase flow; simulation of ice accretion; 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: 2017
• Tom: Vol. 24, No. 2
• Strony: 271--278
• 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]

autor

Sieradzki A.

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

autor

Stalewski W.

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

Bibliografia

• [1] Federal Aviation Regulations FAR 25 Appendix C, http://www.flightsimaviation.com/data/FARS/part_25-appC.html.
• [2] Messinger, B. L., Equilibrium Temperature of an Unheated Icing Surface as a Function of Air Speed, Journal of the Aeronautical Sciences, Jan., pp. 29-42, 1953.
• [3] Myers, T., Extension to the Messinger Model for Aircraft Icing, AIAA Journal, Vol. 39, No. 2, February 2001.
• [4] Morency, F., Brrahimi, M. T., Tezok, F., Paraschivoiu, I., Hot Air Anti-Icing System Modelization in the Ice Prediction Code Canice, AIAA-98-0192, American Institute of Aeronautics and Astronautics, Inc., 1997.
• [5] Beaugendre, H., Morency, F., Habashi, W., Development of a second generation In-Flight Icing Simulation Code, Journal of Fluids Engineering, Vol. 128 (2), pp. 378-387, 2006.
• [6] Hospers, J. M., Hoeijmakers, H. W. M., Numerical Simulation of SLD Ice Accretions, 27th International Congress of the Aeronautical Sciences, 2010.
• [7] 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.

Uwagi

PL

Opracowanie ze środków MNiSW w ramach umowy 812/P-DUN/2016 na działalność upowszechniającą naukę (zadania 2017).