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Development of a Second Generation In-Flight Icing Simulation Code (Keynote)

[+] Author Affiliations
Wagdi G. Habashi, Héloïse Beaugendre, François Morency

McGill University, Montreal, Quebec, Canada

Paper No. FEDSM2003-45816, pp. 1967-1975; 9 pages
doi:10.1115/FEDSM2003-45816
From:
  • ASME/JSME 2003 4th Joint Fluids Summer Engineering Conference
  • Volume 1: Fora, Parts A, B, C, and D
  • Honolulu, Hawaii, USA, July 6–10, 2003
  • Conference Sponsors: Fluids Engineering Division
  • ISBN: 0-7918-3696-7 | eISBN: 0-7918-3673-8
  • Copyright © 2003 by ASME

abstract

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. Such codes predict 2-D sectional ice shapes, which are then manufactured from a light material and attached as disposable profiles on a test aircraft to investigate it for stability and control under icing encounters. Although efficient for calculating ice shapes on simple geometries, current codes encounter major difficulties or simply cannot simulate ice shapes on truly 3D geometries such as nacelles, high-lift wings, engines and systems that combine external and internal flows. Modern Computational Fluid Dynamics (CFD) technologies can overcome many of these difficulties and FENSAP-ICE is such a second generation CFD-based in-flight icing simulation system, bringing to the icing field simulation methods already by the aircraft and turbomachinery industries. It is built in a modular and interlinked fashion to successively solve each of flow, impingement, accretion, heat loads and performance degradation via field models based on the Euler/Navier-Stokes equations for the clean and degraded flow, and new partial differential equations for the other three icing processes. This paper presents the FENSAP-ICE system and shows examples of its use.

Copyright © 2003 by ASME
Topics: Simulation , Flight

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