A study of rotor blade aeroelastic stability was carried out, using an analytic model of a two-dimensional airfoil undergoing dynamic stall and on elastomechanical representation including flapping, flapwise bending and torsional degrees of freedom. Results for a hovering rotor demonstrated that the models used are capable of reproducing both classical and stall flutter. The minimum rotor speed for the occurrence of stall flutter in hover was found to be determined from coupling between torsion and flapping. Instabilities analogous to both classical and stall flutter were found to occur in forward flight. However, the large stall-related torsional oscillations which commonly limit aircraft forward speed appear to be the response to rapid changes in aerodynamic moment which accompany stall and unstall, rather than the result of an aeroelastic instability.


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    Titel :

    Analysis of stall flutter of a helicopter rotor blade.


    Beteiligte:
    Crimi, P. (Autor:in)

    Kongress:

    Structures, Structural Dynamics, and Materials Conference ; 1973 ; Williamsburg, VA, US


    Erscheinungsdatum :

    1973-03-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :





    HELICOPTER ROTOR BLADE STALL DETECTOR

    L VOV NIKOLAJ LEONIDOVICH / KHABAROV STANISLAV SERGEEVICH / NOSOV ANDREJ ANATOL EVICH et al. | Europäisches Patentamt | 2015

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