Application of FENSAP-ICE-Unsteady to Helicopter Icing

Document Number: 2007-01-3310

Date Published: September 2007

Author(s):
Martin S. Aubé - Newmerical Technologies International
Guido S. Baruzzi - Newmerical Technologies International
Wagdi G. Habashi - Newmerical Technologies International
Cristhian N. Aliaga - CFD Lab, McGill University

Abstract:
The applicability of FENSAP-ICE-Unsteady to solve ice accretion on rotating helicopter blades is investigated using a two-bladed rotor and a generic cylinder, to represent a fuselage, for a forward flight test case. The unsteady rime ice accretion is simulated by coupling, at each time step, flow and water drop equations to the Messinger icing model. Mesh displacement effects are taken into account by an Arbitrary Lagrangian-Eulerian method. This new icing model is applied to rotor/fuselage flows by considering two grid domains: the first being fixed around the fuselage, and the second rotating with the blades. The gap region is stitched with tetrahedral elements to fully guarantee flow conservation.

File Size: 470K
Product Status: In Stock

See other papers presented at 2007 SAE Aircraft and Engine Icing International Conference, September 2007, Seville, SPAIN, Session: Rotorcraft In-flight Icing - Part II

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