Numerical analysis of a swept wing hot air ice protection system

Abstract

A tight-coupling heat transfer method is proposed in this paper for the analysis of the performance of the hot air ice protection system. The Eulerian method is used for the calculation of the local collection efficiency. The external heat transfer coefficient was computed using the boundary layer integrated method. The thermal conductivity within the wing skin and the internal heat transfer between the hot air flow and the skin were computed using the computational fluid dynamic method. At the same time, the external heat flux boundary condition and the surface temperature were updated automatically by user-defined function to drive the iteration of the tight-coupling heat transfer calculation. The surface temperature results in dry air condition are compared with flight test data and show agreement. The maximum temperature difference between the simulation and the test is 11.5 K. In addition, the method proposed in this paper is applied to the wing hot air ice protection system of a real aircraft in icing conditions. It is found that the surface temperature ranges from 3 to 30 ℃ under certain flight and icing conditions. Larger droplet diameter or larger liquid water content leads to more runback water which changes the surface temperature not much when the parameters of the bleeding air are the same.

Keywords

Hot air ice protection swept wing tight coupling heat transfer computational fluid dynamics

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References

Civil Aviation Administration of China, Civil aviation regulations of China, Part 25: airworthiness standards for transport category airplanes, 4th ed. Beijing, China: Civil Aviation Administration of China, 2011, pp. 144–144.

Brown

Raghunathan

Watterson

. Heat transfer correlation for anti-icing system. J Aircr 2002; 39: 65–70.

Papadakis M, Wong SH, Yeong HW, et al. Icing tunnel experiments with a hot air anti-icing system. AIAA paper 2008-444, 2008.

Silva

GAL

Silvares

Zerbini

EJGJ

. Numerical simulation of airfoil thermal anti-ice operation part 1: mathematical modeling. J Aircr 2007; 44: 627–634.

Morency

Tezok

Paraschivoiu

. Heat and mass transfer in the case of anti-icing simulation. J Aircr 2000; 37: 245–252.

De Mattos B and Oliveira G. Three-dimensional thermal coupled analysis of a wing slice slat with a piccolo tube. AIAA paper 2000-39841, 2000.

Liu

Hua

. Three-dimensional integrated thermodynamic simulation for wing anti-icing system. J Aircr 2004; 41: 1291–1297.

Croce G, Habashi WG, Guevremont G, et al. 3D Thermal analysis of an anti-icing device using FENSAP-ICE. AIAA paper 1998-0193, 1998.

Wang H, Tran P, Habashi WG, et al. Anti-icing simulation in wet air of a piccolo system using FENSAP-ICE. SAE paper 2007-01-3357, 2007.

10.

Yang SH, Lin GP and Shen XB. An Eulerian method for water droplet impingement prediction and its implementations. In: Proceedings of 2009 international symposium on aircraft airworthiness, Beijing, China, 2–4 November 2009, pp.72–81.

11.

Shen

Lin

Yang

. Analysis on three dimensional water droplets impingement characteristics of engine inlet. J Beijing Univ Aeronaut Astronaut 2011; 37: 1–5.

12.

Messinger

. Equilibrium temperature of an unheated icing surface as a function of air speed. J Aeronaut Sci 1953; 20: 29–42.

13.

Lin

. Coupled heat transfer calculation on an airfoil electrothermal anti-icing surface. J Aerosp Power 2010; 25: 1491–1496.

14.

Bu XQ, Lin GP, Yu J, et al. Numerical simulation of an electrothermal anti-icing system. In: Proc. IMechE, Part G: J Aerospace Engineering. Epub ahead of print 16 October 2012. DOI: 10.1177/0954410012463525.