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Prediction of ice accretion and aerodynamic performance analysis of NACA 2412 aerofoil

Published online by Cambridge University Press:  28 April 2023

M. Ferdous Open the ORCID record for M. Ferdous [Opens in a new window]  and
Md. H. E. Haider Open the ORCID record for Md. H. E. Haider [Opens in a new window]
M. Ferdous*
Affiliation:
Department of Aeronautical Engineering, Military Institute of Science and Technology, Mirpur Cantonment, Dhaka, Bangladesh
Md. H. E. Haider
Affiliation:
Department of Electrical Electronics and Communication Engineering, Military Institute of Science and Technology, Mirpur Cantonment, Dhaka, Bangladesh
*
*Corresponding author. Email: mahbuba@ae.mist.ac.bd
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Abstract

Adverse meteorological conditions often contribute to the formation of ice on aircraft wing section, engine nacelle and other parts leading to the loss of lift coefficient and increase in drag coefficient affecting aircraft control and stability. This paper addresses the problem of in-flight icing on an asymmetric aerofoil under three different ambient and cloud conditions. The study involves prediction of the leading-edge ice thickness using a numerical model developed from the mass and energy conservation law and Messinger freezing fraction model at the same Reynolds number. Later on, degradation in the aerodynamic performance of the iced aerofoil was also investigated using the computational fluid dynamics (CFD) technique, taking the flow field around a 2D aerofoil geometry into account. The aerodynamic study indicates that cumulus clouds embedded with stratified clouds contribute to the formation of mixed ice on aerofoil leading edge and causes the worst icing scenario reducing the lift coefficient to 90% and increasing the drag coefficient to 800% for the same ambient conditions.

Keywords

In-flight icingCloud typeControl volumeLiquid water contentSuper cooled dropletsIce accretionFreezing fractionAngle-of-attack
Type
Research Article
Information
The Aeronautical Journal , Volume 127 , Issue 1313 , July 2023 , pp. 1104 - 1140
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Copyright
© The Author(s), 2023. Published by Cambridge University Press on behalf of Royal Aeronautical Society

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