Methods are presented for estimating some of the more fundamental design variables of single-rotor helicopters (tip speed, blade area, disk loading, and installed power) based on design requirements (speed, weight, fuselage drag, and design hover ceiling). The well-known constraints of advancing-blade compressibility and retreating-blade stall are incorporated into the estimation process, based on an empirical interpretation of rotor performance data from large-scale wind-tunnel tests. Engine performance data are presented and correlated with a simple model usable for preliminary design. When approximate results are required quickly, these methods may be more convenient to use and provide more insight than large digital computer programs.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Helicopter rotor and engine sizing for preliminary performance estimation


    Beteiligte:
    Talbot, P. D. (Autor:in) / Bowles, J. V. (Autor:in) / Lee, H. C. (Autor:in)

    Erscheinungsdatum :

    01.06.1986


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch







    Helicopter health monitoring from engine to rotor

    Marriott, J.F. / Kaye, J.F. | Tema Archiv | 1988


    Helicopter Sizing by Statistics

    Rand, Omri | Online Contents | 2004