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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    Title :

    Wing Divergence of Trimmed Aircraft


    Contributors:
    T. Niblett (author)

    Publication date :

    1986


    Size :

    9 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Wing Divergence of Trimmed Aircraft

    L. T. Niblett | NTIS | 1987



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