Hostname: page-component-586b7cd67f-rcrh6 Total loading time: 0 Render date: 2024-11-28T08:23:25.646Z Has data issue: false hasContentIssue false
  • English
  • Français

Insight into rime ice accretion on an aircraft wing and corresponding effects on aerodynamic performance

Published online by Cambridge University Press:  07 June 2016

Y. Cao ,
J. Huang ,
Z. Xu  and
J. Yin
Y. Cao*
Affiliation:
Institute of Aircraft Design, Beijing University of Aeronautics and Astronautics, Beijing, People's Republic of China
J. Huang
Affiliation:
Institute of Aircraft Design, Beijing University of Aeronautics and Astronautics, Beijing, People's Republic of China
Z. Xu
Affiliation:
Institute of Aircraft Design, Beijing University of Aeronautics and Astronautics, Beijing, People's Republic of China
J. Yin
Affiliation:
Institute of Aircraft Design, Beijing University of Aeronautics and Astronautics, Beijing, People's Republic of China
*
[email protected]
Get access Rights & Permissions [Opens in a new window]

Abstract

A method based on the Eulerian two-phase flow theory to numerically simulate three-dimensional rime ice accretions on an aircraft wing is presented in this paper. The governing equations for supercooled droplet motion under Eulerian framework are established using the droplet pseudo-fluid model. A permeable wall boundary condition is proposed to simulate the phenomenon of droplets impinging on the wing in solving the governing equations for droplets. The local droplet collection efficiency is readily obtained from the droplet flowfield solution in the control volume adjacent to the wing surface. The rime ice accretion can be simulated under the assumption that the droplets freeze immediately as they impinge on the wing surface since the environment temperature is low enough (typically below –15°C). A method to build the ice shape is proposed based on the assumption that ice grows in the direction normal to the wing surface. The rime ice accretion on a GLC-305 swept wing model under some specific conditions has been simulated to validate the present method. Furthermore, different flight conditions, namely, different angles of attack and different angles of sideslip, have been dealt with to investigate their effects on rime ice accretion as well as the corresponding aerodynamic effects.

Keywords

Three-dimensionalrime icetwo-phase flowpermeable wallnumerical simulation
Type
Research Article
Information
The Aeronautical Journal , Volume 120 , Issue 1229 , July 2016 , pp. 1101 - 1122
Copyright
Copyright © Royal Aeronautical Society 2016 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

REFERENCES

1.Ruff, G.A. and Berkowitz, B.M.User's Manual for the NASA Lewis Ice Accretion Prediction Code (LEWICE). NASA CR 185129, 1990.Google Scholar
2.Wright, W.B.Update to the NASA Lewis Ice Accretion Code LEWICE. NASA CR 195387, 1994.Google Scholar
3.Wright, W.B. Validation results for LEWICE 3.0. AIAA paper 2005-1243, 2005.Google Scholar
4.Gent, R.W. TRAJICE2 – A combined water droplet trajectory and ice accretion prediction program for aerofoils. RAE TR 90054, 1990.Google Scholar
5.Hedde, T. and Guffond, D. ONERA three-dimensional icing model. AIAA J., 1995, 33, (6), pp 1038–1045.Google Scholar
6.Hedde, T. and Guffond, D. Improvement of the ONERA 3D Icing Code, Comparison with 3D experimental shapes. AIAA paper 1993-0169, 1993.CrossRefGoogle Scholar
7.Mingione, G., Brandi, V. and Esposito, B. Ice accretion prediction on multi-element airfoils. AIAA paper 1997-0177, 1997.CrossRefGoogle Scholar
8.Louchez, P., Fortin, G., Mingione, G.et al. Beads and rivulets modeling in ice accretion on a wing. AIAA paper 1998-0489, 1997.CrossRefGoogle Scholar
9.Mingione, G. and Brandi, V. A 3D ice accretion simulation code. AIAA paper 1999-0247, 1999.Google Scholar
10.Cao, Y., Zhang, Q. and Sheridan, J.Numerical simulation of rime ice accretions on an airfoil using an Eulerian method. Aeronautical J., 2008, 112, (1131), pp 243–249.CrossRefGoogle Scholar
11.Zhou, L. X.Theory and Numerical Modeling of Turbulent Gas-Particle Flows and Combustion, Science Press and CRC Press, New York, New York, US, 1993.Google Scholar
12.Cao, Y., Guo, Z. and Chao, M.Numerical simulation of ice accretion prediction on multiple element airfoil. Science China Technological Sciences, 2011, 54, (9), 2296–2304.Google Scholar
13.Shen, X., Lin, G.et al.Three-dimensional numerical simulation of ice accretion at the engine inlet. J. Aircr., 2013, 50, (2), pp 635–642.CrossRefGoogle Scholar
14.Bourgault, Y., Boutanios, Z. and Habashi, W.G.Three-dimensional Eulerian approach to droplet impingement simulation using FENSAP-ICE, Part 1: model, algorithm, and validation. J. Aircr., 2000, 37, (1), pp 95–103.Google Scholar
15.Beaugendre, H., Morency, F., Baruzzi, G.S. and Habashi, W.G. FENSAP-ICE: A comprehensive 3D simulation system for in-flight icing. AIAA paper 2001-2566, 2001.Google Scholar
16.Beaugendre, H., Morency, F. and Habashi, W.G.FENSAP-ICE's three-dimensional in-flight ice accretion module: ICE3D, J. Aircr., 2003, 40, (2), pp 239–247.Google Scholar
17.Jones, W.P. and Launder, B.E.The prediction of laminarization with a two-equation model of turbulence, Int. J. Heat Mass Transfer, 1972, 15, (2), pp 301–304.Google Scholar
18.Patankar, S.V.Numerical Heat Transfer and Fluid Flow, 1980, McGraw-Hill, New York, New York, US, pp 131–134.Google Scholar
19.Zhu, J. and Rodi, W.A low-dispersion and bounded convection scheme. Computer Methods in Applied Mechanics and Engineering, 1991, 92, pp 87–96.CrossRefGoogle Scholar
20.Launder, B.E. and Spalding, D.B.The numerical computation of turbulent flows. Computer Methods in Applied Mechanics and Engineering, 1974, 3, pp 269–289.Google Scholar
21.Snellen, M., Boelens, O.J. and Hoeijmakers, H.W.M.A Computational method for numerically simulating ice accretion. AIAA paper 1997-2206, 1997.Google Scholar
22.Sherrie, I.K., Robert, T.B. and Christopher, I. R. CFL3D USER'S Manual. NASA-TM-1998-208444, 1998.Google Scholar
23.Khosla, P.K. and Rubin, S.G.A diagonally dominant second order accurate implicit scheme. Computers & Fluids, 1974, 2, pp 207–209.Google Scholar
24.Papadakis, M., Yeong, H.W., Wong, S.C., Vargas, M. and Potapczuk, M.G. Aerodynamic performance of a swept wing with ice accretions. AIAA Paper 2003-0731, 2003.Google Scholar