Icing is a meteorological hazard that may affect aircraft and helicopter operations due to supercooled droplets that impinge on the front parts of the different structures. A three-dimensional icing model has been developed at ONERA to calculate ice accretion shapes for aerodynamic components that can not be predicted using conventional two-dimensional codes. It is described, emphasizing the original parts with respect to the two-dimensional existing models. The model includes Euler inviscid flow calculation. Droplet trajetories are calculated in a three-dimensional grid. The remesh on the leading edge is adapted to follow aerodynamics singularities. The boundary layer is calculated using a mixing length formulaton to model the wall roughness influence on convective heat transfer. Runback paths are integrated. The heat balance is calculated in a grid created along the runback paths. The domain of validity of the three-dimensional icing code is described; compared with the two-dimensional model this domain is wider, especially for high speeds. The three-dimensional model is shown to simulate well a uniform ice deposit on a three-dimensional rotor blade tip. Then, a comparison of the three- and two-dimensional codes on an infinite swept wing shows that the corrected two-dimensional code predicts the catch efficiency but not the ice shape. Finally, it is shown that the continuum flux hypothesis prevents the three-dimensional model from simulating correctly the 'lobster tail' ice shape (nonuniform ice deposit).


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    Title :

    ONERA three-dimensional icing model


    Additional title:

    ONERA - Dreidimensionales Eismodell


    Contributors:
    Hedde, T. (author) / Guffond, D. (author)

    Published in:

    AIAA Journal ; 33 , 6 ; 1038-1045


    Publication date :

    1995


    Size :

    8 Seiten, 16 Bilder, 1 Tabelle, 14 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




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