In a rotary-wing aircraft blade airfoil included in a rotary-wing aircraft such as a helicopter, it is assumed that: a position of a rear end of a chord of the airfoil with respect to a front end of the chord is 100% chord; a position of a blade upper surface, the position being measured from the chord, is an upper blade height; and a position of a blade lower surface, the position being measured from the chord, is a lower blade height. The rotary-wing aircraft blade airfoil satisfies the following four conditions: a first airfoil condition, which is a condition that a blade thickness has its maximum value at a position within a range from 30% chord to 40% chord; a second airfoil condition, which is a condition that 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 airfoil condition, which is a condition that the upper blade height has its maximum value at a position within a range from 25% chord to 35% chord; and a fourth airfoil condition, which is a condition that the lower blade height has its maximum value at a position within a range from 35% chord to 45% chord.


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    Title :

    回転翼航空機用ブレード翼型、このブレード翼型を有するブレード、およびこのブレードを備える回転翼航空機


    Publication date :

    2019-12-25


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Japanese


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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