Title: Development of a three-dimensional icing simulation code in the NSMB flow solver

Authors: Dorian Pena; Yannick Hoarau; Éric Laurendeau

Addresses: Laboratoire des sciences de l'ingénieur, de l'informatique et de l'imagerie (ICUBE), Équipe MECAFLU, Université de Strasbourg, 4 Rue Blaise Pascal, 67400 Strasbourg, France; Département de Génie Mécanique, École Polytechnique de Montréal, C.P. 6079, Centre-Ville, Montréal (QC), H3C 3A7, Canada ' Laboratoire des sciences de l'ingénieur, de l'informatique et de l'imagerie (ICUBE), Équipe MECAFLU, Université de Strasbourg, 4 Rue Blaise Pascal, 67400 Strasbourg, France ' Département de Génie Mécanique, École Polytechnique de Montréal, C.P. 6079, Centre-Ville, Montréal (QC), H3C 3A7, Canada

Abstract: An icing model is developed in the Navier-Stokes multi-block (NSMB) compressible solver. The code implemented in this study is based on an Eulerian formulation for droplets tracking solved implicitly by means of CGSTAB or SIP methods, a modified iterative Messinger model using an improved water runback scheme for ice thickness calculation and three-dimensional mesh deformation to track the ice/air interface through time. The whole process is parallelised with MPI for efficient calculations. Validation is performed on several test cases including NACA23012 and NACA00012 airfoils and ONERA-M6 swept wing. Pressure coefficients around iced 23012 airfoil are compared with experimental data. Rime icing is computed on a DLR-F6 wing/body configuration. In all studied cases, the results are in good agreement with the literature.

Keywords: aircraft icing; Eulerian droplet transport equations; icing effect; 3D modelling; simulation; NSMB flow solver; icing models; water runback; ice thickness; 3D mesh deformation; ice-air interface tracking; airfoils; swept wing; rime icing.

DOI: 10.1504/IJESMS.2016.075544

International Journal of Engineering Systems Modelling and Simulation, 2016 Vol.8 No.2, pp.86 - 98

Received: 30 Jun 2014
Accepted: 01 Apr 2015

Published online: 30 Dec 2015 *

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