A main rotor blade exhibiting a unique planform shape in which the blade chord increases from the root end of the blade inboard region to the outer main region of the blade, where the blade chord achieves a maximum chord at a spanwise location within the main region, then decreases toward a distal tip end. The leading edge preferably is generally straight while the trailing edge is contoured to define the chord. Another characteristic feature of the rotor blade design is the location of the blade-feathering axis in which the feathering axis is located at a mid chord position over some inboard length of the rotor blade then transitions to a quarter chord location. Another characteristic feature is an airfoil distribution along the blade span that transitions from a blunt trailing edge to a sharp trailing edge airfoil suited for mid-range Mach number operation. The tip region preferably utilizes a transonic flow airfoil. Another characteristic feature of the rotor blade design is an unconventional combination of positive and negative twist gradients.


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    Titel :

    ROTOR BLADE FOR A HIGH SPEED ROTARY-WING AIRCRAFT


    Weitere Titelangaben:

    ROTORBLATT FÜR EIN HOCHGESCHWINDIGKEITS-DREHFLÜGELFLUGZEUG
    PALE DE ROTOR POUR AÉRONEF À VOILURE TOURNANTE DE VITESSE ÉLEVÉE


    Beteiligte:
    BAGAI ASHISH (Autor:in) / MOFFITT ROBERT C (Autor:in) / BLACKWELL ROBERT H (Autor:in) / KRAUSS TIMOTHY A (Autor:in)

    Erscheinungsdatum :

    2017-10-11


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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