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Calibration of the 13- by 13-inch adaptive wall test section for the Langley 0.3-meter transonic cryogenic tunnelA 13 by 13 inch adaptive wall test section was installed in the 0.3 Meter Transonic Cryogenic Tunnel circuit. This new test section is configured for 2-D airfoil testing. It has four solid walls. The top and bottom walls are flexible and movable whereas the sidewalls are rigid and fixed. The wall adaptation strategy employed requires the test section wall shapes associated with uniform test section Mach number distributions. Calibration tests with the test section empty were conducted with the top and bottom walls linearly diverged to approach a uniform Mach number distribution. Pressure distributions were measured in the contraction cone, the test section, and the high speed diffuser at Mach numbers from 0.20 to 0.95 and Reynolds numbers from 10 to 100 x 10 (exp 6)/per foot.
Document ID
19910004148
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Mineck, Raymond E. (NASA Langley Research Center Hampton, VA, United States)
Hill, Acquilla S. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
December 1, 1990
Subject Category
Research And Support Facilities (Air)
Report/Patent Number
L-16787
NASA-TP-3049
NAS 1.60:3049
Accession Number
91N13461
Funding Number(s)
PROJECT: RTOP 505-61-21-03
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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