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Journal of Fluids Engineering 128, 2 (2006) 378-387
Development of a second generation in-flight icing simulation code
Héloïse Beaugendre ( ) 1, 2, 3, François Morency 3, W. G. Habashi 3
(2006)

Two-dimensional and quasi-3D in-flight ice accretion simulation codes have been widely used by the aerospace industry for the last two decades as an aid to the certification process. The present paper proposes an efficient numerical method for calculating ice shapes on simple or complex 3D geometries. The resulting ice simulation system, FENSAP-ICE, is built in a modular fashion to successively solve each flow, impingement and accretion via field models based on partial differential equations (PDEs). The FENSAP-ICE system results are compared to other numerical and experimental results on 2D and slightly complex 3D geometries. It is concluded that FENSAP-ICE gives results in agreement with other code calculation results, for the geometries available in the open literature.
1 :  Institut de Mathématiques de Bordeaux (IMB)
CNRS : UMR5251 – Université Sciences et Technologies - Bordeaux I – Université Victor Segalen - Bordeaux II
2 :  MC2 (INRIA Bordeaux - Sud-Ouest)
INRIA – Université Sciences et Technologies - Bordeaux I – Université Victor Segalen - Bordeaux II – CNRS : UMR
3 :  CFD Lab, Department of Mechanical Engineering
McGill University
Informatique/Modélisation et simulation

Informatique/Logiciel mathématique

Physique/Mécanique/Génie mécanique

Sciences de l'ingénieur/Mécanique/Génie mécanique

Physique/Mécanique/Mécanique des fluides

Sciences de l'ingénieur/Mécanique/Mécanique des fluides
Ducted fan engine – Helicopter – Helicopter rotor – Ice – Geometrical shape – Aerofoil – Icing – Numerical simulation – Modeling – Computation code – Airplane – Aircraft – Three dimensional flow
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