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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    Titel :

    Aerodynamics of Rotating-wing Aircraft with Blade-pitch Control


    Beteiligte:
    Pfluger, A (Autor:in)

    Erscheinungsdatum :

    01.02.1940


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch




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