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Two-dimensional aerodynamic characteristics of the NACA 0012 airfoil in the Langley 8 foot transonic pressure tunnelData are presented for lift coefficients from near zero through maximum values at Mach numbers from 0.30 to 0.86 and Reynolds numbers of 3.0 x 10 to the sixth power with transition fixed. A limited amount of data is presented near zero and maximum lift for a Reynolds number of 6.0 x 10 to the sixth power with transition fixed. In addition, transition free data is presented through the Mach number range from 0.30 to 0.86 for near zero lift and a Reynolds number of 3.0 x 10 to the sixth power.
Document ID
19810014503
Document Type
Technical Memorandum (TM)
Authors
Harris, C. D. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
April 1, 1981
Subject Category
AERODYNAMICS
Report/Patent Number
NASA-TM-81927
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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NameType 19810014503.pdf STI