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High Reynolds Number tests of the NASA SC(2)-0012 airfoil in the Langley 0.3-meter transonic cryogenic tunnelA wind-tunnel investigation of the NASA SC(2)-0012 airfoil has been conducted in the Langley 0.3-Meter Transonic Cryogenic Tunnel. This investigation supplements the two-dimensional airfoil studies of the Advanced Technology Airfoil Test Program. The Mach number was varied from 0.60 to 0.84. The stagnation temperature and pressure were varied to provide a Reynolds number range from 6 to 40 x 10 to the 6th power based on a 6.0-in. (15.24-cm) airfoil chord. No corrections for wind-tunnel wall interference have been made to the data. The aerodynamic results are presented as integrated force and moment coefficients and pressure distributions without any analysis.
Document ID
19870014161
Document Type
Technical Memorandum (TM)
Authors
Mineck, Raymond E. (NASA Langley Research Center Hampton, VA, United States)
Lawing, Pierce L. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
July 1, 1987
Subject Category
AERODYNAMICS
Report/Patent Number
NAS 1.15:89102
L-16259
NASA-TM-89102
Funding Number(s)
PROJECT: RTOP 505-61-01-02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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NameType 19870014161.pdf STI