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 |