Various existing unsteady aerodynamic strip theories which have been developed in the past for both fixed and rotary wing aeroelastic analyses are modified in the paper so as to make them applicable to the coupled flap-lag-torsional aeroelastic problem of a rotor blade in hover. These corrections are primarily due to constant angle of attack, constant inflow and variable free stream velocity due to lead-lag motion. Next, the modified strip theories are incorporated in a coupled flap-lag-torsional aeroelastic analysis of the rotor blade in hover and the sensitivity of the aeroelastic stability boundaries to the aerodynamic assumptions is examined.


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    Titel :

    Effect of modified aerodynamic strip theories on rotor blade aeroelastic stability


    Beteiligte:
    Friedmann, P. (Autor:in) / Yuan, C. (Autor:in)

    Kongress:

    Structures, Structural Dynamics, and Materials Conference ; 1976 ; King of Prussia, PA


    Erscheinungsdatum :

    01.01.1976


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :