Measurements were made of the unsteady normal force and pitching moment on an NACA 0012 airfoil model oscillated both sinusoidally and nonsinusoidally over a range of incidence angles, including a substantial penetration into stall. The sinusoidal normal force and pitching moment data were reduced and tabulated as functions of the angle of attack, the angular velocity parameter, and the angular acceleration parameter. This generalized form of the data was used to reconstruct the measured sinusoidal aerodynamic response of the model airfoil with excellent results. Additional correlations were made using nonsinusoidal pitch schedules which included periodic ramp changes in angle of attack and a flexured angular blade response to a one-per-rev sinusoidal incidence angle change typical of that for a helicopter blade. The agreement between predicted and measured normal force and moment loops was very good for the ramp motion. (Author)


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Investigation of Airfoil Dynamic Stall and Its Influence on Helicopter Control Loads


    Beteiligte:
    F. O. Carta (Autor:in) / G. L. Commerford (Autor:in) / R. G. Carlson (Autor:in) / R. H. Blackwell (Autor:in)

    Erscheinungsdatum :

    1972


    Format / Umfang :

    208 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Investigation of Helicopter Control Loads Induced by Stall Flutter

    P. J. Arcidiacono / F. O. Carta / L. M. Casellini et al. | NTIS | 1970


    Adaptive Airfoil Dynamic Stall Control

    Kerho, Michael | AIAA | 2005


    Adaptive Airfoil Dynamic Stall Control

    Kerho, M. | Online Contents | 2007


    Adaptive Airfoil Dynamic Stall Control

    Kerho, M. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2005


    Adaptive Airfoil Dynamic Stall Control

    Michael Kerho | AIAA | 2007