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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]
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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 

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