@Article{icces.2021.08298,
AUTHOR = {Koji Fukudome, Takuya Wada, Toma Takahashi, Makoto Yamamoto},
TITLE = {Numerical Simulation of Glaze Ice Formation  with Accompanied by Water Film Flow Using E-MPS Method},
JOURNAL = {The International Conference on Computational \& Experimental Engineering and Sciences},
VOLUME = {23},
YEAR = {2021},
NUMBER = {1},
PAGES = {9--9},
URL = {http://www.techscience.com/icces/v23n1/42024},
ISSN = {1933-2815},
ABSTRACT = {Icing is a phenomenon that super-cooled droplets impinge and accrete 
on a solid surface. When the icing occurs on aircraft wings, it deteriorates
aerodynamic performances of the wings and the blade cascades of the engine, 
which may lead to severe accidents. Although number of investigations have 
been performed both experimentally and numerically [1], the icing shape 
prediction is now not practically complete due to the complex aspect of icing 
phenomena. In the previous research, Toba et al. [2] employed an explicitmoving particles simulation method (referred as E-MPS method), which was 
based on the Lagrangian approach, to reproduce the icing process of supercooled water droplets impinging on the NACA0012 airfoil. This E-MPS method 
enables us to reproduce complex ice shapes such as so-called feather and largescale surface roughness which are difficult to be reproduced by the conventional 
grid-based method [3]. However, in the glaze ice condition, droplets form a thin 
water film and then solidify after running along the blade surface, so that it is 
needed to treat the water film behavior to obtain the icing shape. In the present 
study, the icing simulation method with the E-MPS method was improved to be 
able to reproduce a water film behavior. The present method was validated for 
the glaze icing on a flat plate, and then it was successfully applied to the glaze 
icing on the NACA0012 airfoil.},
DOI = {10.32604/icces.2021.08298}
}