Record Details

Flow Angularity Measurements in the NASA-Langley Transonic Dynamics Tunnel
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Author and Affiliation:
Yeager, William T., Jr.(Army Research Lab., Vehicle Technology Directorate, Hampton, VA, United States);
Wilbur, Matthew L.(Army Research Lab., Vehicle Technology Directorate, Hampton, VA, United States);
Mirick, Paul H.(Army Research Lab., Vehicle Technology Directorate, Hampton, VA, United States);
Rivera, Jose A., Jr.(NASA Langley Research Center, Hampton, VA, United States)
Abstract: An 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.
Publication Date: Dec 01, 2005
Document ID:
20060004732
(Acquired Feb 02, 2006)
Subject Category: AERODYNAMICS
Report/Patent Number: NASA/TM-2005-213946, ARL-TR-3691, L-19195
Document Type: Technical Report
Financial Sponsor: NASA Langley Research Center; Hampton, VA, United States
Organization Source: NASA Langley Research Center; Hampton, VA, United States
Army Research Lab.; Vehicle Technology Directorate; Hampton, VA, United States
Description: 61p; In English; Original contains black and white illustrations
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: No Copyright
NASA Terms: FLOW MEASUREMENT; TEST CHAMBERS; TRANSONIC WIND TUNNELS; DYNAMIC PRESSURE; FLOW DISTRIBUTION; MACH NUMBER; SURVEYS
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