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.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

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


    Contributors:

    Publication date :

    1948


    Size :

    18 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English