Development of a second generation in-flight icing simulation code

Héloïse Beaugendre (1, 2, 3) , François Morency (3) , W. G. Habashi (3)

1 IMB - Institut de Mathématiques de Bordeaux
2 MC2 - Modélisation, contrôle et calcul
3 CFD Lab [Montréal]

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.

Mots clés: Ducted fan engine; Helicopter; Helicopter rotor; Ice; Geometrical shape; Aerofoil; Icing; Numerical simulation; Modeling; Computation code; Airplane; Aircraft; Three dimensional flow

Domaines: Modélisation et simulation; Logiciel mathématique [cs.MS]; Génie mécanique [physics.class-ph]; Génie mécanique [physics.class-ph]; Mécanique des fluides [physics.class-ph]; Mécanique des fluides [physics.class-ph]

Héloïse Beaugendre, François Morency, W. G. Habashi. Development of a second generation in-flight icing simulation code. Journal of Fluids Engineering, 2006, 128 (2), pp.378-387. ⟨inria-00337571⟩