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Numerical simulation of rime ice accretions on an aerofoil using an Eulerian method

Published online by Cambridge University Press:  03 February 2016

Y. Cao ,
Q. Zhang  and
J. Sheridan
Y. Cao
Affiliation:
Institute of Aircraft Design, Beijing University of Aeronautics and Astronautics, Beijing, China
Q. Zhang
Affiliation:
Institute of Aircraft Design, Beijing University of Aeronautics and Astronautics, Beijing, China
J. Sheridan
Affiliation:
Department of Mechanical and Aerospace Engineering, Monash University, Australia
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Abstract

Based on two-phase flow theory, an Eulerian method to simulate rime ice accretions on an aerofoil has been developed. The SIMPLE (semi-implicit method for pressure linked equations) algorithm on a collocated grid is employed to solve the governing equations for the airflow. In order to simulate droplets impinging on an aerofoil, a permeable wall is proposed to solve the governing equations for supercooled droplets. The collection efficiency and impingement limits are obtained from the droplets’ flowfield. The process of ice accretion is simulated using the assumption that ice accumulates layer-by-layer and the ice shape is predicted with the assumption that ice grows in the direction normal to the aerofoil surface. The rime ice accretions on a NACA0012 aerofoil at 0° and 4° angles-of-attack have been investigated and there is agreement between the simulated results and previously published experimental data. The change of the pressure coefficient along the iced aerofoil is also analysed.

Type
Research Article
Information
The Aeronautical Journal , Volume 112 , Issue 1131 , May 2008 , pp. 243 - 249
Copyright
Copyright © Royal Aeronautical Society 2008 

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