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Description and calibration of the Langley 6- by 19-inch transonic tunnelA description and calibration is presented of the Langley 6- by 19-inch transonic tunnel which is a two-dimensional facility with top and bottom slotted walls used for testing two-dimensional airfoil sections. Basic tunnel-empty Mach number distributions and schlieren flow photographs as well as integrated normal-force coefficients, pitching-moment coefficients, surface-pressure distributions, and schlieren flow photographs of an NACA 0012 airfoil calibration model are presented. The Mach number capability of the facility is from 0.5 to about 1.1 with a corresponding Reynolds number range of 1.5 million to 3 million based on a 4.0-in. model chord. Comparisons of experimental results from the tests with previous data are also presented.
Document ID
19730014612
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Ladson, C. L. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 2, 2013
Publication Date
May 1, 1973
Subject Category
Facilities, Research, And Support
Report/Patent Number
L-8680
NASA-TN-D-7182
Accession Number
73N23339
Funding Number(s)
PROJECT: RTOP 501-06-05-02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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