The effect of a simulated glaze-ice accretion on the aerodynamic performance of a NACA 0012 airfoil was studied experimentally. Two ice shapes were tested: one from an experimentally measured accretion, and one from an accretion predicted using a computer model given the same icing conditions. Lift, drag, and pitching moment were measured for the airfoil with both smooth and rough ice shapes. The ice shapes caused large lift and drag penalties, primarily due to large separation bubbles. Surface pressure distributions clearly showed the regions of separated flow. The aerodynamic performance of the two shapes compared well at positive, but not negative, angles of attack.


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    Titel :

    Experimental aerodynamic characteristics of an NACA 0012 airfoil with simulated glaze ice


    Beteiligte:
    Bragg, M. B. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    01.09.1988



    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :



    Experimental aerodynamic characteristics of an NACA 0012 airfoil with simulated ice

    KORKAN, K. D. / CROSS, E. J. / CORNELL, C. C. | AIAA | 1985



    Experimental aerodynamic characteristics of an NACA 0012 airfoil with simulated ice

    Korkan, K. D. / Cross, E. J., Jr. / Cornell, C. C. | NTRS | 1985


    Experimental aerodynamic characteristics of NACA 0012 airfoils with simulated glaze and rime ice

    Cuerno-Rejado, C / López-Martínez, G / Escudero-Arahuetes, J L et al. | SAGE Publications | 2001