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Low-speed aerodynamic characteristics of a 14-percent-thick NASA phase 2 supercritical airfoil designed for a lift coefficient of 0.7The low speed aerodynamic characteristics of a 14 percent thick supercritical airfoil are documented. The wind tunnel test was conducted in the Low Turbulence Pressure Tunnel. The effects of varying chord Reynolds number from 2,000,000 to 18,000,000 at a Mach number of 0.15 and the effects of varying Mach number from 0.10 to 0.32 at a Reynolds number of 6,000,000 are included.
Document ID
19830013896
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Harris, C. D. (NASA Langley Research Center Hampton, VA, United States)
Mcghee, R. J. (NASA Langley Research Center Hampton, VA, United States)
Allison, D. O. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
December 1, 1980
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-81912
L-13891
NAS 1.15:81912
Accession Number
83N22167
Funding Number(s)
PROJECT: RTOP 505-31-33-04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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