A rotary-wing aircraft blade airfoil for use with a rotary-wing aircraft such as a helicopter. The airfoil satisfies the following four conditions: a first condition in which a blade thickness has its maximum value at a position within a range from 30% chord to 40% chord; a second condition in which a camber has its maximum value at a position within a range from 15% chord to 25% chord, and that a slope of the camber changes from decreasing into increasing at a position within a range from 45% chord to 55% chord; a third condition in which the upper blade height has its maximum value at a position within a range from 25% chord to 35% chord; and a fourth condition in which the lower blade height has its maximum value at a position within a range from 35% chord to 45% chord.


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    Titel :

    ROTARY-WING AIRCRAFT BLADE AIRFOIL, BLADE HAVING THE BLADE AIRFOIL, AND ROTARY-WING AIRCRAFT INCLUDING THE BLADE


    Beteiligte:
    YASUDA HIDEMASA (Autor:in) / TSUJIUCHI TOMOKA (Autor:in) / ABE AKIHITO (Autor:in) / OCHI AKIO (Autor:in)

    Erscheinungsdatum :

    2021-08-05


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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