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16-foot transonic tunnel test section flowfield surveyA flow survey has been made of the test section of the NASA Langley Research Center 16-Foot Transonic Tunnel at subsonic and supersonic speeds. The survey was performed using five five-hole pyramid-head probes mounted at 14 inch intervals on a survey rake. Probes were calibrated at freestream Mach numbers from 0.50 to 0.95 and from 1.18 to 1.23. Flowfield surveys were made at Mach numbers from 0.50 to 0.90 and at Mach 1.20. The surveys were made at tunnel stations 130.6, 133.6, and 136.0. By rotating the survey rake through 180 degrees, a cylindrical volume of the test section 4.7 feet in diameter and 5.4 feet long centered about the tunnel centerline was surveyed. Survey results showing the measured test section upflow and sideflow characteristics and local Mach number distributions are presented. The report documents the survey probe calibration techniques used, summarizes the procedural problems encountered during testing, and identifies the data discrepancies observed during the post-test data analysis.
Document ID
19950014253
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Yetter, J. A. (NASA Langley Research Center Hampton, VA, United States)
Abeyounis, W. K. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
December 1, 1994
Subject Category
Research And Support Facilities (Air)
Report/Patent Number
NAS 1.15:109157
NASA-TM-109157
Accession Number
95N20669
Funding Number(s)
PROJECT: RTOP 538-05-13-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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