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Effect of a Rapid Blade-Pitch Increase on the Thrust and Induced-Velocity Response of a Full-Scale Helicopter RotorA method has been proposed for predicting the effect of a rapid blade-pitch increase on the thrust and induced-velocity response of a helicopter rotor. General equations have been derived for the ensuing motion of the helicopter. These equations yield time histories of thrust, induced velocity, and helicopter vertical velocity for given rates of blade-pitch-angle changes and given rotor-angular-velocity time histories. The results of the method have been compared with experimental results obtained with a rotor mounted on the Langley helicopter test tower. The calculated and experimental results are in good agreement, although, in general, the calculated thrust-coefficient overshoots are about 10 percent greater than those obtained experimentally.
Document ID
19930083686
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Technical Note
Authors
Carpenter, Paul J
(National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Fridovich, Bernard
(National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Date Acquired
August 16, 2013
Publication Date
November 1, 1953
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NACA-TN-3044
Accession Number
93R12976
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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