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Effect of advanced rotorcraft airfoil sections on the hover performance of a small-scale rotor modelA hover test was conducted on a small scale rotor model for two sets of tapered rotor blades. The baseline rotor blade set used a NACA 0012 airfoil section, whereas the second rotor blade set had advanced rotorcraft airfoils distributed along the radius. The experiment was conducted for a range of thrust coefficients and tip speeds, and the data were compared to the predictions of three analytical methods. The data show the advantage of the advanced airfoils at the higher rotor thrust levels; two of the analyses predicted the correct data trends.
Document ID
19890014893
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Althoff, Susan L. (Army Aviation Systems Command Hampton, VA., United States)
Date Acquired
September 5, 2013
Publication Date
September 1, 1988
Subject Category
Aerodynamics
Report/Patent Number
AVSCOM-TP-88-B-001
NAS 1.60:2832
L-16407
NASA-TP-2832
Accession Number
89N24264
Funding Number(s)
PROJECT: RTOP 505-61-51-10
PROJECT: DA PROJ. 1L1-61102-AH-45-A
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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