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Lifting surface theory for a helicopter rotor in forward flightA lifting surface theory was developed for a helicopter rotor in forward flight for compressible and incompressible flow. The method utilizes the concept of the linearized acceleration potential and makes use of the vortex lattice procedure. Calculations demonstrating the application of the method are given in terms of the lift distribution on a single rotor, a two-bladed rotor, and a rotor with swept-forward and swept-back tips. In addition, the lift on a rotor which is vibrating in a pitching mode at 4/rev is given. Compressibility effects and interference effects for a two-bladed rotor are discussed.
Document ID
19850002608
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Tai, H.
(NASA Langley Research Center Hampton, VA, United States)
Runyan, H. L.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
September 1, 1984
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.15:86315
NASA-TM-86315
Report Number: NAS 1.15:86315
Report Number: NASA-TM-86315
Meeting Information
Meeting: Decennial Specialists'' Meeting on Rotorcraft Dyn.
Location: Moffett Field, CA
Country: United States
Start Date: November 7, 1984
End Date: November 9, 1984
Accession Number
85N10916
Funding Number(s)
PROJECT: RTOP 505-33-43-09
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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