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.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Wing Divergence and Structural Distortion


    Beteiligte:
    L. T. Niblett (Autor:in)

    Erscheinungsdatum :

    1985


    Format / Umfang :

    30 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Wing Divergence of Trimmed Aircraft

    T. Niblett | NTIS | 1986


    Wing Divergence of Trimmed Aircraft

    L. T. Niblett | NTIS | 1987


    Wing Divergence and Rolling Power

    L. T. Niblett | NTIS | 1988


    Divergence of an Inflated Wing

    Peter Crimi | AIAA | 2000


    The estimation of wing divergence speeds

    Broadbent, E. G. | TIBKAT | 1948