By means of a simple theoretical model it is shown that wing divergence of a free aircraft can be defined using the static case of trimmed level flight. The same model also shows that the control angle per 'g' goes to zero at a speed near the fixed-root divergence speed and that there is a large change in the spanwise distribution of airload in going from a low speed to speeds above that of fixed-root divergence.


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    Titel :

    Wing Divergence of Trimmed Aircraft


    Beteiligte:
    T. Niblett (Autor:in)

    Erscheinungsdatum :

    1986


    Format / Umfang :

    9 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Wing Divergence of Trimmed Aircraft

    L. T. Niblett | NTIS | 1987



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