NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Reynolds number tests of an NPL 9510 airfoil in the Langley 0.3-meter transonic cryogenic tunnelAn investigation of the NPL 9510 airfoil was conducted in the Langley 0.3-Meter Transonic Cryogenic Tunnel over the following ranges of test conditions: Mach number 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 airfoil chord of 1.34 x 10 to the 6th power to 48.23 x 10 to the 6th power, and angle of attack of 0 deg to 6 deg. The drag creep previously reported by the British National Physics Laboratory at low Reynolds numbers was also found to be present at high Reynolds numbers; the section drag coefficient continued to decrease even at the highest Reynolds number tested. Tests made close to free-stream saturation did not produce altered aerodynamic coefficients due to condensation effects.
Document ID
19840003073
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
L-15585
NASA-TM-85663
NAS 1.15:85663
Accession Number
84N11141
Funding Number(s)
PROJECT: RTOP 534-02-13-16
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
No Preview Available