A computational code has been developed for aeroelastic analysis for an all-movable horizontal tail, and a companion wind-tunnel test program has been conducted. The structural bending and torsional stiffness are based upon an experimental tail model that has served as the basis for free-play design criteria. A linear three-dimensional time-domain vortex-lattice aerodynamic model is used to study the flutter and also nonlinear limit-cycle oscillations induced by a free-play gap in the actuating mechanism at the root of the tail as well as the effects of the root rotation angle (nominal angle of attack) on limit-cycle-oscillation response and gravity loads. It is found that the root rotation angle, gravity loads, and the initial conditions all significantly affect the limit-cycle-oscillation behavior. The computed aeroelastic responses are compared with the experimental data.


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    Titel :

    Computational/Experimental Aeroelastic Study for a Horizontal-Tail Model with Free Play


    Beteiligte:
    Tang, Deman (Autor:in) / Dowell, Earl H. (Autor:in)

    Erschienen in:

    AIAA Journal ; 51 , 2 ; 341-352


    Erscheinungsdatum :

    01.02.2013




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch