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Aerodynamic characteristics of two rotorcraft airfoils designed for application to the inboard region of a main rotor bladeA wind tunnel investigation was conducted to determine the 2-D aerodynamic characteristics of two new rotorcraft airfoils designed especially for application to the inboard region of a helicopter main rotor blade. The two new airfoils, the RC(4)-10 and RC(5)-10, and a baseline airfoil, the VR-7, were all studied in the Langley Transonic Tunnel at Mach nos. from about 0.34 to 0.84 and at Reynolds nos. from about 4.7 to 9.3 x 10 (exp 6). The VR-7 airfoil had a trailing edge tab which is deflected upwards 4.6 degs. In addition, the RC(4)-10 airfoil was studied in the Langley Low Turbulence Pressure Tunnel at Mach nos. from 0.10 to 0.44 and at Reynolds nos. from 1.4 to 5.4 x 10 (exp 6) respectively. Some comparisons were made of the experimental data for the new airfoils and the predictions of two different theories. The results of this study indicates that both of the new airfoils offer advantages over the baseline airfoil. These advantages are discussed.
Document ID
19900014923
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Noonan, Kevin W.
(Army Aerostructures Directorate Hampton, VA., United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1990
Subject Category
Aerodynamics
Report/Patent Number
NASA-TP-3009
NAS 1.60:3009
L-16737
AVSCOM-TR-90-B-005
Accession Number
90N24239
Funding Number(s)
PROJECT: RTOP 505-61-59-76
PROJECT: DA PROJ. 1L1-62211-A-47-AA
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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