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Experimental investigation of a 10-percent-thick helicopter rotor airfoil section designed with a viscous transonic analysis codeAn investigation was conducted in the Langley 6- by 28-Inch Transonic Tunnel to determine the two dimensional aerodynamic characteristics of a 10-percent-thick helicopter rotor airfoil at Mach numbers from 0.33 to 0.87 and respective Reynolds numbers from 4.9 x 10 to the 6th to 9.8 x 10 to the 6th. This airfoil, designated the RC-10(N)-1, was also investigated at Reynolds numbers from 3.0 x 10 to the 6th to 7.3 x 10 to the 6th at respective Mach numbers of 0.33 to 0.83 for comparison wit the SC 1095 (with tab) airfoil. The RC-10(N)-1 airfoil was designed by the use of a viscous transonic analysis code. The results of the investigation indicate that the RC-10(N)-1 airfoil met all the design goals. At a Reynolds number of about 9.4 x 10 to the 6th the drag divergence Mach number at zero normal-force coefficient was 0.815 with a corresponding pitching-moment coefficient of zero. The drag divergence Mach number at a normal-force coefficient of 0.9 and a Reynolds number of about 8.0 x 10 to the 6th was 0.61. The drag divergence Mach number of this new airfoil was higher than that of the SC 1095 airfoil at normal-force coefficients above 0.3. Measurements in the same wind tunnel at comparable Reynolds numbers indicated that the maximum normal-force coefficient of the RC-10(N)-1 airfoil was higher than that of the NACA 0012 airfoil for Mach numbers above about 0.35 and was about the same as that of the SC 1095 airfoil for Mach numbers up to 0.5.
Document ID
19830022118
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Noonan, K. W. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
July 1, 1981
Subject Category
Aerodynamics
Report/Patent Number
AVRADCOM-TR-81-B-3
NASA-TP-1864
L-14182
NAS 1.60:1864
Accession Number
83N30389
Funding Number(s)
PROJECT: RTOP 505-31-33-05
PROJECT: DA PROJ. 1L1-61102-AH-45
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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