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Helicopter rotor and engine sizing for preliminary performance estimationMethods are presented for estimating some of the more fundamental design variables of single-rotor helicopters (tip speed, blade area, disk loading, and installed power) based on design requirements (speed, weight, fuselage drag, and design hover ceiling). The well-known constraints of advancing-blade compressibility and retreating-blade stall are incorporated into the estimation process, based on an empirical interpretation of rotor performance data from large-scale wind-tunnel tests. Engine performance data are presented and correlated with a simple model usable for preliminary design. When approximate results are required quickly, these methods may be more convenient to use and provide more insight than large digital computer programs.
Document ID
19860058091
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Talbot, P. D.
(NASA Ames Research Center Moffett Field, CA, United States)
Bowles, J. V.
(NASA Ames Research Center Moffett Field, CA, United States)
Lee, H. C.
(NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 12, 2013
Publication Date
June 1, 1986
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 86-1756
Accession Number
86A42829
Distribution Limits
Public
Copyright
Other

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