Two blunt trailing edge airfoil sections were tested in a transonic wind tunnel and their aerodynamic characteristics compared with those of a conventional NACA 64-106 section previously tested under identical conditions. The two blunt sections used a segmented trailing edge geometry to minimize their base drag. This segmented trailing edge geometry consisted of isolated rectangular blocks protruding downstream from the base with splitter plates spanning the spaces between the blocks. Both blunt sections had superior transonic stability, greater resistance to separation, and greater bending strength than the NACA section. One of the blunt sections also had less drag than the NACA section over the whole test range of lift coefficients for a significant portion of the transonic Mach number range. (Author)


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Transonic Wind Tunnel Tests on Two Blunt Trailing Edge Aerofoils


    Beteiligte:
    N. Pollock (Autor:in)

    Erscheinungsdatum :

    1974


    Format / Umfang :

    29 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Wind tunnel tests on aerofoils at negative incidences

    Clark, K. W. ;Lockspeiser, B. | SLUB | 1930


    Wind tunnel tests of aerofoils with pilot planes

    Bradfield, F. B. ;Clark, K. W. | SLUB | 1929


    Wind tunnel tests on aerofoils at negative incidences

    Clark, K. W. / Lockspeiser, B. | TIBKAT | 1931


    Wind tunnel tests of aerofoils R.A.F. 38 and 48

    Clark, K. W. ;Wood, W. E. | SLUB | 1933


    Wind tunnel tests of aerofoils R.A.F. 38 and 48

    Clark, K. W. / Wood, W. E. | TIBKAT | 1933