Apparatus was developed which utilized a pitching airplane model to determine maximum wing loads as a function of the rate of change of angle of attack. In order to evaluate the pitching-model technique, maximum lift coefficients were determined in wind-tunnel investigations of a l% scale model of a conventional single-engine fighter airplane and were 20 compared with existing flight data for this airplane. The wind-tunnel investigation extended through a Mach number range from approximately 0.2 to 0.6 at pitching velocities comparable to flight values obtained with the test airplane in abrupt pull-ups. The wind-tunnel and flight results were found to be in good agreement.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Investigation of the Variation of Maximum Lift for a Pitching Airplane Model and Comparison With Flight Results


    Beteiligte:
    P. W. Harper (Autor:in) / R. E. Flanigan (Autor:in)

    Erscheinungsdatum :

    1948


    Format / Umfang :

    18 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch