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 Sound and Vibration v 4 n 3 Nov 1966 p 388-402)
Wing-rotor interactions
J Aircraft
Journal of Aircraft ; 3 , n 4
1966
7 pages
Aufsatz (Zeitschrift)
Englisch
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Engineering Index Backfile | 1966
|AIAA | 1966
|ratum: ""Wing-Rotor Interactions""
AIAA | 1967
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