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 moment coefficients were measured for the airfoil with both ice shapes, smooth and rough. The aerodynamic performance of the two shapes compared well at positive, but not negative, angles of attack. Split hot-film probe velocity data were presented in the upper surface boundary layer and in the wake. Boundary layer parameters were presented for the separation bubble and in the reattached turbulent boundary layer.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Experimental measurements in a large separation bubble due to a simulated glaze ice shape


    Additional title:

    Experimentelle Messungen in einer grossen Trennungsblase, verursacht durch eine simulierte geglaettete Eisform


    Contributors:

    Published in:

    AIAA-Papers ; Jan ; 1-15


    Publication date :

    1988


    Size :

    15 Seiten, 24 Bilder, 19 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English