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Flow Angularity Measurements in the NASA-Langley Transonic Dynamics TunnelAn investigation using a survey rake with 11 five-hole pyramid-head probes has been conducted in the Langley Transonic Dynamics Tunnel (TDT) to measure the test section flow angularity. Flow measurements were made in a 10-ft square grid centered about the test section centerline at a single streamwise location for nine Mach numbers ranging from 0.50 to 1.19 at dynamic pressures of 100 and 225 pounds per square foot. Test section flow angularity was found to be minimal with a generally random flow pattern. Corrections for survey rake induced in-plane flow were determined to be necessary; however, corrections for rake induced lift effects were not required.
Document ID
20060004732
Document Type
Technical Memorandum (TM)
Authors
Yeager, William T., Jr. (Army Research Lab. Hampton, VA, United States)
Wilbur, Matthew L. (Army Research Lab. Hampton, VA, United States)
Mirick, Paul H. (Army Research Lab. Hampton, VA, United States)
Rivera, Jose A., Jr. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 7, 2013
Publication Date
December 1, 2005
Subject Category
Aerodynamics
Report/Patent Number
L-19195
NASA/TM-2005-213946
ARL-TR-3691
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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