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Development of a Rotating Rake Array for Boundary-Layer-Ingesting Fan-Stage MeasurementsThe recent Boundary-Layer-Ingesting Inlet/Distortion Tolerant Fan wind tunnel experiment at NASA Glenn Research Center's 8- by 6-foot Supersonic Wind Tunnel (SWT) examined the performance of a novel inlet and fan stage that was designed to ingest the vehicle boundary layer in order to take advantage of a predicted overall propulsive efficiency benefit. A key piece of the experiment's instrumentation was a pair of rotating rake arrays located upstream and downstream of the fan stage. This paper examines the development of these rake arrays. Pre-test numerical solutions were sampled to determine placement and spacing for rake pressure and temperature probes. The effects of probe spacing and survey density on the repeatability of survey measurements was examined. These data were then used to estimate measurement uncertainty for the adiabatic efficiency.
Document ID
20180000118
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Wolter, John D.
(NASA Glenn Research Center Cleveland, OH, United States)
Arend, David J.
(NASA Glenn Research Center Cleveland, OH, United States)
Hirt, Stefanie M.
(NASA Glenn Research Center Cleveland, OH, United States)
Gazzaniga, John A.
(ZIN Technologies, Inc. Middleburg Heights, OH, United States)
Date Acquired
January 5, 2018
Publication Date
December 1, 2017
Subject Category
Aircraft Propulsion And Power
Aerodynamics
Report/Patent Number
NASA/TM-2017-219553
E-19405
GRC-E-DAA-TN45816
AIAA Paper 2017-4636
Meeting Information
Meeting: AIAA Propulsion and Energy Forum and Exhibition
Location: Atlanta, GA
Country: United States
Start Date: July 10, 2017
End Date: July 12, 2017
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
CONTRACT_GRANT: NNC12BA01B
WBS: WBS 081876.02.03.50.06.02
Distribution Limits
Public
Copyright
Public Use Permitted.
Keywords
turbomachinery
adiabatic effciency
instrumentation
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