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Aerodynamic characteristics of three helicopter rotor airfoil sections at Reynolds number from model scale to full scale at Mach numbers from 0.35 to 0.90An investigation was conducted in the Langely 6 by 28 inch transonic tunnel to determine the two dimensional aerodynamic characteristics of three helicopter rotor airfoils at Reynolds numbers from typical model scale to full scale at Mach numbers from about 0.35 to 0.90. The model scale Reynolds numbers ranged from about 700,00 to 1,500,000 and the full scale Reynolds numbers ranged from about 3,000,000 to 6,600,000. The airfoils tested were the NACA 0012 (0 deg Tab), the SC 1095 R8, and the SC 1095. Both the SC 1095 and the SC 1095 R8 airfoils had trailing edge tabs. The results of this investigation indicate that Reynolds number effects can be significant on the maximum normal force coefficient and all drag related parameters; namely, drag at zero normal force, maximum normal force drag ratio, and drag divergence Mach number. The increments in these parameters at a given Mach number owing to the model scale to full scale Reynolds number change are different for each of the airfoils.
Document ID
19800023826
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Noonan, K. W. (NASA Langley Research Center Hampton, VA, United States)
Bingham, G. J. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
September 1, 1980
Subject Category
Aerodynamics
Report/Patent Number
NASA-TP-1701
L-13139
AVRADCOM-TR-80-B-5
Report Number: NASA-TP-1701
Report Number: L-13139
Report Number: AVRADCOM-TR-80-B-5
Accession Number
80N32333
Funding Number(s)
PROJECT: RTOP 505-31-33-02
PROJECT: DA PROJ. 1L1-61102-AH-45
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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