Use of wing to unload helicopter rotor is discussed for cases with and without auxiliary propulsion; data are presented from flight test of five wing-rotor combinations showing effects of wing on performance, stability and control, structural loads, and maneuver characteristics of machines; major problem areas associated with winged helicopter operation, i.e., rotor speed and roll control during autorotation and autorotation entry, are described and defined analytically; means of minimizing effects are noted; it is concluded that use of wing is advantageous for rotorcraft with maximum speed above approximately 140 knots; design considerations and guide to wing size selection are given. (See also J of Aircraft v 3 n 4 July-Aug 1966 p 326-32)


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    Title :

    Wing-rotor interactions


    Additional title:

    J Sound Vibration


    Contributors:
    Lynn, R.R. (author)

    Published in:

    Publication date :

    1966


    Size :

    15 pages



    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English


    Keywords :


    Wing-rotor interactions

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