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Sidewall Mach Number Distributions for the NASA Langley Transonic Dynamics TunnelThe Transonic Dynamics Tunnel(TDT) was recalibrated due to the conversion of the heavy gas test medium from R-12 to R-134a. The objectives of the tests were to determine the relationship between the free-stream Mach number and the measured test section Mach number, and to quantify any necessary corrections. Other tests included the measurement of pressure distributions along the test-section walls, test-section centerline, at certain tunnel stations via a rake apparatus, and in the tunnel settling chamber. Wall boundary layer, turbulence, and flow angularity measurements were also performed. This paper discusses the determination of sidewall Mach number distributions.
Document ID
20010064082
Document Type
Technical Memorandum (TM)
Authors
Florance, James R. (NASA Langley Research Center Hampton, VA United States)
Rivera, Jose A., Jr. (NASA Langley Research Center Hampton, VA United States)
Date Acquired
September 7, 2013
Publication Date
June 1, 2001
Subject Category
Aircraft Design, Testing and Performance
Report/Patent Number
NASA/TM-2001-211019
L-18085
NAS 1.15:211019
Funding Number(s)
PROJECT: RTOP 706-31-41-02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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