Experimental investigation was conducted of effect of pitching rate and pitching axis location on aerodynamic loading of two-dimensional airfoil during nonoscillatory pitching motion to large angle of attack; selected test results, believed to be applicable to helicopter blade experiencing dynamic stall, are presented; rate of change of angle of attack is established as dominant factor determining very large peak lift and moment acting on airfoil during stall process.


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    Title :

    Dynamic stall considerations in helicopter rotors


    Additional title:

    Am Helicopter Soc -- J


    Contributors:
    Ham, N.D. (author) / Garelick, M.S. (author)


    Publication date :

    1968


    Size :

    7 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


    Dynamic Stall Considerations in Helicopter Rotors

    N. D. Ham / M. S. Garelick | NTIS | 1968




    Investigations of dynamic stall and dynamic stall control on helicopter airfoils

    Gardner, Anthony D. / Technische Universität Clausthal | TIBKAT | 2015

    Free access

    Investigations of dynamic stall and dynamic stall control on helicopter airfoils

    Gardner, Anthony D. / Technische Universität Clausthal | TIBKAT | 2016