Record Details

Sidewall Mach Number Distributions for the NASA Langley Transonic Dynamics Tunnel
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Author and Affiliation:
Florance, James R.(NASA Langley Research Center, Hampton, VA United States);
Rivera, Jose A., Jr.(NASA Langley Research Center, Hampton, VA United States)
Abstract: The 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.
Publication Date: Jun 01, 2001
Document ID:
20010064082
(Acquired Jul 20, 2001)
Subject Category: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
Report/Patent Number: NASA/TM-2001-211019, NAS 1.15:211019, L-18085
Document Type: Technical Report
Contract/Grant/Task Num: RTOP 706-31-41-02
Financial Sponsor: NASA Langley Research Center; Hampton, VA United States
Organization Source: NASA Langley Research Center; Hampton, VA United States
Description: 78p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: No Copyright
NASA Terms: TRANSONIC WIND TUNNELS; CALIBRATING; FLOW MEASUREMENT; PRESSURE MEASUREMENT; TURBULENT FLOW; TEST CHAMBERS; PRESSURE DISTRIBUTION; MACH NUMBER; FREE FLOW
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