PROBLEM TO BE SOLVED: To provide a leading edge of an airfoil that may reduce or avoid the existence of geometric features causing a laminar flow to transition to a non-laminar flow.SOLUTION: An airfoil 150 may include a leading edge 200 and a shape control mechanism 400. The leading edge may include a flexible leading edge skin 214 having a first end 216, a second end 218, and an arc length defined therebetween. The shape control mechanism may be attached to the flexible leading edge skin at a plurality of support locations 224 and may transition the flexible leading edge skin from a first shape 228 having a first curvature profile 230 to a second shape 232 having a second curvature profile 234 different than the first curvature profile without a change in the arc length.

    【課題】層流を非層流に遷移させる幾何学的特性の存在を減少させ、又は回避しうる、翼の前縁部を提供する。【解決手段】翼150は、前縁部200と形状制御機構400とを含みうる。前縁部は、第1端部216と第2端部218、及び、それらの間に画定された弧長を有する、可撓性前縁外板214を含みうる。形状制御機構は、複数の支持位置224で可撓性前縁外板に取り付けられ、かつ、可撓性前縁外板を、第1湾曲プロファイル230を有する第1形状228から、第1湾曲プロファイルとは異なる第2湾曲プロファイル234を有する第2形状232へと、弧長の変化なく遷移させうる。【選択図】図4


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    Title :

    MORPHING AIRFOIL LEADING EDGE


    Additional title:

    翼前縁部をモーフィングすること


    Contributors:

    Publication date :

    2015-12-03


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Japanese


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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