Publication Date:
2019-07-13
Description:
The 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.
Keywords:
Aircraft Propulsion and Power; Aerodynamics
Type:
NASA/TM-2017-219553
,
AIAA Paper 2017-4636
,
E-19405
,
GRC-E-DAA-TN45816
,
AIAA Propulsion and Energy Forum and Exhibition; Jul 10, 2017 - Jul 12, 2017; Atlanta, GA; United States
Format:
application/pdf
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