Results of pressure-distribution tests on airfoil with conventional trailing edge flap, which were made in atmospheric wind tunnel; maximum chord loadings were obtained with flap displaced downward and with airfoil at large angles of attack; greater changes were produced in normal force and in center of pressure travel by upflap than by equal downflap displacement.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Wind tunnel pressure distribution tests on an airfoil with trailing edge flap


    Weitere Titelangaben:

    Nat. Advisory Committee Aeronautics -- Tech. Note


    Beteiligte:
    Wenzinger, C.J. (Autor:in) / Loeser, Jr., O. (Autor:in)


    Erscheinungsdatum :

    1929


    Format / Umfang :

    10 pages


    Anmerkungen:

    10 Figs., Bibliography


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :