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Low-speed aerodynamic characteristics of a 9.3-percent-thick supercritical airfoil sectionAn investigation was conducted in the Langley low turbulence pressure tunnel to determine the low-speed, two dimensional characteristics of a 9.3 percent-thick supercritical airfoil. The airfoil was tested at Reynolds numbers (based on chord) from 2.9 million to 16.8 million, at Mach numbers from 0.10 to 0.36, and at geometric angles of attack from -8 degrees to 14 degrees.
Document ID
19830002798
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Noonan, K. W. (NASA Langley Research Center Hampton, VA, United States)
Mcghee, R. J. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
August 1, 1982
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-X-72763
NAS 1.15:X-72763
Report Number: NASA-TM-X-72763
Report Number: NAS 1.15:X-72763
Accession Number
83N11068
Funding Number(s)
PROJECT: RTOP 505-06-31-02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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