Attention is given to the results of NASA-sponsored rotorcraft icing research which was aimed at the formulation of a predictive method for the computation of performance penalties due to rotor and airfoil icing. Parametric simulated ice test results obtained in wind tunnels are compared with those of other investigations. These comparisons indicate that proper design of simulated ice shapes can adequately represent ice on airfoil sections, with incremental lift, drag, and pitching moments matching those generated in icing wind tunnels.


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    Title :

    The performance characteristics of simulated ice on rotorcraft airfoils


    Contributors:
    Flemming, R. J. (author) / Shaw, R. J. (author) / Lee, J. D. (author)

    Publication date :

    1985-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




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