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Variable camber rotor studyDeployment of variable camber concepts on helicopter rotors was analytically assessed. It was determined that variable camber extended the operating range of helicopters provided that the correct compromise can be obtained between performance/loads gains and mechanical complexity. A number of variable camber concepts were reviewed on a two dimensional basis to determine the usefulness of leading edge, trailing edge and overall camber variation schemes. The most powerful method to vary camber was through the trailing edge flaps undergoing relatively small motions (-5 deg to +15 deg). The aerodynamic characteristics of the NASA/Ames A-1 airfoil with 35% and 50% plain trailing edge flaps were determined by means of current subcritical and transonic airfoil design methods and used by rotor performance and loads analysis codes. The most promising variable camber schedule reviewed was a configuration with a 35% plain flap deployment in an on/off mode near the tip of a blade. Preliminary results show approximately 11% reduction in power is possible at 192 knots and a rotor thrust coefficient of 0.09. The potential demonstrated indicates a significant potential for expanding the operating envelope of the helicopter. Further investigation into improving the power saving and defining the improvement in the operational envelope of the helicopter is recommended.
Document ID
19830011469
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Dadone, L.
(Boeing Vertol Co. Philadelphia, PA, United States)
Cowan, J.
(Boeing Vertol Co. Philadelphia, PA, United States)
Mchugh, F. J.
(Boeing Vertol Co. Philadelphia, PA, United States)
Date Acquired
September 4, 2013
Publication Date
August 1, 1982
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NAS 1.26:166382
D210-11938-1
NASA-CR-166382
Accession Number
83N19740
Funding Number(s)
CONTRACT_GRANT: NAS2-10768
PROJECT: RTOP 505-03-11
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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