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An unsteady helicopter rotor-fuselage aerodynamic interaction analysisA computational method has been developed to treat the unsteady aerodynamic interaction between a helicopter rotor, wake, and fuselage. Two existing codes, a lifting line-prescribed wake rotor analysis and a source panel fuselage analysis, were modified and coupled to allow prediction of unsteady fuselage pressures and airloads. A prescribed displacement technique was developed to position the rotor wake about the fuselage. Also coupled into the method were optional blade dynamics or rigid blade performance analyses to set the rotor operating conditions. Sensitivity studies were performed to determine the influence of the wake and fuselage geometry on the computational results. Solutions were computed for an ellipsoidal fuselage and a four bladed rotor at several advance ratios, using both the classical helix and the generalized distorted wake model. Results are presented that describe the induced velocities, pressures, and airloads on the fuselage and the induced velocities and bound circulation at the rotor. The ability to treat arbitrary geometries was demonstrated using a simulated helicopter fuselage. Initial computations were made to simulate the geometry of an experimental rotor-fuselage interaction study performed at the Georgia Institute of Technology.
Document ID
19900058268
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Lorber, Peter F.
(United Technologies Research Center East Hartford, CT, United States)
Egolf, T. Alan
(United Technologies Research Center East Hartford, CT, United States)
Date Acquired
August 14, 2013
Publication Date
July 1, 1990
Publication Information
Publication: American Helicopter Society, Journal
Volume: 35
ISSN: 0002-8711
Subject Category
Aerodynamics
Accession Number
90A45323
Funding Number(s)
CONTRACT_GRANT: NAS1-17469
Distribution Limits
Public
Copyright
Other

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