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Pressure distributions from high Reynolds number transonic tests of an NACA 0012 airfoil in the Langley 0.3-meter transonic cryogenic tunnelTests were conducted in the 2-D test section of the Langley 0.3-meter Transonic Cryogenic Tunnel on a NACA 0012 airfoil to obtain aerodynamic data as a part of the Advanced Technology Airfoil Test (ATAT) program. The test program covered a Mach number range of 0.30 to 0.82 and a Reynolds number range of 3.0 to 45.0 x 10 to the 6th power. The stagnation pressure was varied between 1.2 and 6.0 atmospheres and the stagnation temperature was varied between 300 K and 90 K to obtain these test conditions. Tabulated pressure distributions and integrated force and moment coefficients are presented as well as plots of the surface pressure distributions. The data are presented uncorrected for wall interference effects and without analysis.
Document ID
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Ladson, Charles L.
(NASA Langley Research Center Hampton, VA, United States)
Hill, Acquilla S.
(NASA Langley Research Center Hampton, VA, United States)
Johnson, William G., Jr.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
December 1, 1987
Subject Category
Report/Patent Number
NAS 1.15:100526
Accession Number
Funding Number(s)
PROJECT: RTOP 505-61-01-02
Distribution Limits
Work of the US Gov. Public Use Permitted.
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