A model for each of the basic flow elements involved in the unsteady stall of a two-dimensional airfoil in incompressible flow is presented. The interaction of these elements is analyzed using a digital computer. Computations of the loading during transient and sinusoidal pitching motions are in good qualitative agreement with measured loads. The method was used to confirm that large torsional response of helicopter blades detected in flight tests can be attributed to dynamic stall.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    A method for analyzing dynamic stall of helicopter rotor blades


    Contributors:
    Crimi, P. (author) / Reeves, B. L. (author)

    Publication date :

    1972-05-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English


    Keywords :


    A method for analyzing dynamic stall of helicopter rotor blades

    Crimi, Peter / Reeves, Barry L. | TIBKAT | 1972



    DEVICE FOR INDICATING STALL IN HELICOPTER ROTOR BLADES

    MUKHIN IVAN EFIMOVICH / SELEZNEV STANISLAV LEONIDOVICH / DMITRIEV PAVEL VALENTINOVICH et al. | European Patent Office | 2017

    Free access


    Helicopter Dynamic Stall Suppression Using Piezoelectric Active Fiber Composite Rotor Blades

    Wilkie, W. / Park, K. / Belvin, W. et al. | British Library Conference Proceedings | 1998