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)
Wing-rotor interactions
J Sound Vibration
Journal of Sound and Vibration ; 4 , n 3
1966
15 pages
Article (Journal)
Electronic Resource
English
© Metadata Copyright Elsevier B. V. All rights reserved.
Engineering Index Backfile | 1966
|AIAA | 1966
|ratum: ""Wing-Rotor Interactions""
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