In the present report, with the aid of the usual computation methods, a rotor is investigated the pitch of whose blades is capable of being controlled in such a manner that it varies linearly with the flapping angle. To test the effect of this linkage on the aircraft performance, the theory is applied to an illustrative example.


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    Title :

    Aerodynamics of Rotating-wing Aircraft with Blade-pitch Control


    Contributors:
    Pfluger, A (author)

    Publication date :

    1940-02-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English




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