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A 0.15-scale study of configuration effects on the aerodynamic interaction between main rotor and fuselageHover and forward flight tests were conducted to investigate the mutual aerodynamic interaction between the main motor and fuselage of a conventional helicopter configuration. A 0.15-scale Model 222 two-bladed teetering rotor was combined with a 0.15-scale model of the NASA Ames 40x80-foot wind tunnel 1500 horsepower test stand fairing. Configuration effects were studied by modifying the fairing to simulate a typical helicopter forebody. Separation distance between rotor and body were also investigated. Rotor and fuselage force and moment as well as pressure data are presented in graphical and tabular format. Data was taken over a range of thrust coefficients from 0.002 to 0.007. In forward flight speed ratio was varied from 0.1 to 0.3 with shaft angle varying from +4 to -12 deg. The data show that the rotors effect on the fuselage may be considerably more important to total aircraft performance than the effect of the fuselage on the rotor.
Document ID
19880003080
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Trept, Ted (Textron Bell Helicopter Fort Worth, TX, United States)
Date Acquired
September 5, 2013
Publication Date
January 1, 1984
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-166577
NAS 1.26:166577
Accession Number
88N12462
Funding Number(s)
CONTRACT_GRANT: NAS2-11268
PROJECT: RTOP 532-06-11
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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