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Tabulation of data from tests of an NPL 9510 airfoil in the Langley 0.3-meter transonic cryogenic tunnelThe tabulated data from tests of a six inch chord NPL 9510 airfoil in the Langley 0.3-Meter Transonic Cryogenic Tunnel. The tests were performed over the following range of conditions: Mach numbers of 0.35 to 0.82, total temperature of 94 K to 300 K, total pressure of 1.20 to 5.81 atm, Reynolds number based on chord of 1.34 x 10 to the 6th to 48.23 x 10 to the 6th, and angle of attack of 0 deg to 6 deg. The NPL 9510 airfoil was observed to have decreasing drag coefficient up to the highest test Reynolds number.
Document ID
19840005083
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Jenkins, R. V. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
November 1, 1983
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-84579
NAS 1.15:84579
Accession Number
84N13151
Funding Number(s)
PROJECT: RTOP 534-02-13-16
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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