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.


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    Title :

    Helicopter rotor and engine sizing for preliminary performance estimation


    Contributors:
    Talbot, P. D. (author) / Bowles, J. V. (author) / Lee, H. C. (author)

    Publication date :

    1986-06-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English







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