Analysis and testing were conducted in the Langley Transonic Dynamics Tunnel to investigate the aeromechanical stability of a soft inplane hingeless rotor model. Rotor stability data were obtained in hover and in forward flight up to an advanced ratio of 0.35. Model rotor parameters evaluated were blade sweep and droop, pre-cone of the blade feathering axis, and blade pitch-flap coupling. Data obtained during these tests are presented without analysis. Keywords: Hovering; Hingeless helicopter rotor dynamics; Helicopter rotor blades; Ground resonance.


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    Title :

    Experimental Investigation of the Aeromechanical Stability of a Hingeless Rotor in Hover and Forward Flight


    Contributors:

    Publication date :

    1987


    Size :

    20 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English