A rotor blade for an aircraft includes first and second blade tips, a blade body, and a vortex-generating blade. The blade body has an end forming the first blade tip of the rotor blade and an airfoil section configured such that during rotation, pressure acting on a lower surface of the blade body is greater than pressure acting on an upper surface of the blade body. The vortex-generating blade is disposed at an end of the rotor blade and forms the second blade tip. The vortex-generating blade also has an airfoil section configured such that during rotation, pressure acting on a lower surface of the vortex-generating blade is smaller than pressure acting on an upper surface of the vortex-generating blade.


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    Title :

    ROTOR BLADE FOR AIRCRAFT


    Contributors:

    Publication date :

    2020-02-06


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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