Static aeroelastic equations are formulated for an aircraft performing idealized pull-out and rolling maneuvers. It is concluded from the solutions of these equations that an unaugmented aircraft flying at speeds near the fixed-root divergence speed of its wing suffers low values of control angle per g and control effectiveness in roll and that the distribution of incidence across the wing varies considerably with speed.


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    Title :

    Wing Divergence and Structural Distortion


    Contributors:

    Publication date :

    1985


    Size :

    30 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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