Flight test results of minimum autorotative descent rate are compared with calculations based on the minimum power required for steady level flight. Empirical correction factors are derived that account for differences in energy dissipation between these two flight conditions. A method is also presented for estimating the minimum power coefficient for level flight for any helicopter for use in the empirical estimation procedure of autorotative descent rate.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    A Simple Method for Estimating Minimum Autorotative Descent Rate of Single Rotor Helicopters


    Beteiligte:
    P. D. Talbot (Autor:in) / L. G. Schroers (Autor:in)

    Erscheinungsdatum :

    1978


    Format / Umfang :

    17 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch





    Rapid Method for Computing Reachable Landing Distances in Helicopter Autorotative Descent

    Eberle, Brian F. / Rogers, Jonathan D. / Alam, Mushfiqul et al. | AIAA | 2022


    AUTOROTATIVE ENHANCEMENT SYSTEM

    SMITH DUDLEY E / HITTE CORY M / MARSHALL BRYAN et al. | Europäisches Patentamt | 2017

    Freier Zugriff

    AUTOROTATIVE ENHANCEMENT SYSTEM

    SMITH DUDLEY E / HITTE CORY M / MARSHALL BRYAN et al. | Europäisches Patentamt | 2016

    Freier Zugriff

    Autorotative enhancement system

    FENNY CARLOS ALEXANDER / HITTE CORY M / MARSHALL BRYAN et al. | Europäisches Patentamt | 2016

    Freier Zugriff