A rotary wing aircraft includes a single main rotor hub configured to receive a rotor blade. The rotor blade includes a blade root, a blade tip, and a blade body. The blade body includes a leading edge and a trailing edge and defines a feathering axis. The leading edge and the trailing edge each include a first portion and a second portion that extend toward a first direction and a second portion, respectively. At a given radial location along the feathering axis, a local twist angle changes from a positive value to a negative value, a chord length decreases in value, a distance between the trailing edge and the feathering axis decreases in value, and the first portion of the leading edge extends toward the first direction. The rotor blade assembly also includes a trailing edge assembly having a trailing edge flap configured to be selectively deployed by an actuator.


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    Title :

    HIGH SPEED ROTOR BLADE DESIGN


    Contributors:

    Publication date :

    2023-10-12


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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