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An unsteady helicopter rotor: Fuselage interaction analysisA computational method was developed to treat unsteady aerodynamic interactions between a helicopter rotor, wake, and fuselage and between the main and tail rotors. An existing lifting line prescribed wake rotor analysis and a source panel fuselage analysis were coupled and modified to predict unsteady fuselage surface pressures and airloads. A prescribed displacement technique is used to position the rotor wake about the fuselage. Either a rigid blade or an aeroelastic blade analysis may be used to establish rotor operating conditions. Sensitivity studies were performed to determine the influence of the wake fuselage geometry on the computation. Results are presented that describe the induced velocities, pressures, and airloads on the fuselage and on the rotor. The ability to treat arbitrary geometries is demonstrated using a simulated helicopter fuselage. The computational results are compared with fuselage surface pressure measurements at several locations. No experimental data was available to validate the primary product of the analysis: the vibratory airloads on the entire fuselage. A main rotor-tail rotor interaction analysis is also described, along with some hover and forward flight.
Document ID
19880019496
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
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
September 5, 2013
Publication Date
September 1, 1988
Publication Information
Publisher: NASA
Subject Category
Aeronautics (General)
Report/Patent Number
NASA-CR-4178
NAS 1.26:4178
R88-956977-15
Accession Number
88N28880
Funding Number(s)
PROJECT: RTOP 505-61-51
CONTRACT_GRANT: NAS1-17469
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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