Stall flutter of helicopter rotor in simulated forward flight was found to occur in all forward flight cases involving appreciable blade stall, and consisted almost entirely of blade motion in torsional mode; stall flutter amplitude was found to be dependent on such parameters as blade chordwise center of gravity position, torsional damping, torsional frequency, and degree of stall occuring over rotor disk.
Experimental investigation of stall flutter
Am Helicopter Soc -- J
American Helicopter Society -- Journal ; 7 , n 1
1962
14 pages
Aufsatz (Zeitschrift)
Englisch
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NTIS | 1987
|AIAA | 1973
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NTRS | 1971
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