Second harmonic control on the helicopter rotor

dc.contributor.author	W. Stewart	en_US
dc.date.accessioned	2014-10-21T15:54:09Z
dc.date.available	2014-10-21T15:54:09Z
dc.date.issued	1952	en_US
dc.identifier.other	ARC/R&M-2997	en_US
dc.identifier.uri	https://reports.aerade.cranfield.ac.uk/handle/1826.2/3564
dc.description.abstract	The application of second harmonic control on a helicopter rotor causes a redistribution of the loading over the disc. This can be utilised to postpone the forward speed limitations imposed by stalling of the retreating blade. This report develops the theory for second harmonic control. The resultant flapping motion and subsequent incidence distribution depend mainly on blade inertia number. A practical check on the flapping with a full-scale rotor on a testing tower gave excellent agreement with the theory.	en_US
dc.relation.ispartofseries	Aeronautical Research Council Reports & Memoranda	en_US
dc.title	Second harmonic control on the helicopter rotor	en_US