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.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Wing Divergence of Trimmed Aircraft


    Contributors:

    Publication date :

    1987


    Size :

    9 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Wing Divergence of Trimmed Aircraft

    T. Niblett | NTIS | 1986



    Trimmed Flight States of an Over-Actuated Tilt-Wing Aircraft for Linear Controller Synthesis

    Krimphove, Johannes / Schutt, Marten / Osterloh, Patrick et al. | IEEE | 2023



    Minimization of Wing Deformation in Trimmed Flight of Highly Flexible Aircraft Using Multiple Control Surfaces

    Yagil, Leeran / Raveh, Daniella | British Library Conference Proceedings | 2016