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Data from tests of a R4 airfoil in the Langley 0.3-meter transonic cryogenic tunnelAerodynamic data for the DFVLR R4 airfoil are presented in both graphic and tabular form. The R4 was tested in the Langley 0.3-Meter Transonic Cryogenic Tunnel (TCT) at Mach number from 0.60 to 0.78 at angles of attack from -2.0 to 8.0 degrees. The airfoil was tested at Reynolds numbers of 4, 6, 10, 15, 30, and 40 million based on the 152.32 mm chord.
Document ID
19840025314
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Jenkins, R. V. (NASA Langley Research Center Hampton, VA, United States)
Johnson, W. G., Jr. (NASA Langley Research Center Hampton, VA, United States)
Hill, A. S. (NASA Langley Research Center Hampton, VA, United States)
Mueller, R. (Deutsche Forshungs- und Versuchsanstalt fuer Luftund Raumfahrt)
Redeker, G. (Deutsche Forschungs- und Versuchsanstalt fuer Luft- und Raumfahrt)
Date Acquired
September 4, 2013
Publication Date
September 1, 1984
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-85739
NAS 1.15:85739
Accession Number
84N33385
Funding Number(s)
PROJECT: RTOP 505-31-53-10
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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