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Hot gas ingestion test results of a two-poster vectored thrust concept with flow visualization in the NASA Lewis 9- by 15-foot low speed wind tunnelA 9.2 percent scale STOVL hot gas ingestion model was tested in the NASA Lewis 9 x 15-foot Low-Speed Wind Tunnel. Flow visualization from the Phase 1 test program, which evaluated the hot ingestion phenomena and control techniques, is covered. The Phase 2 test program evaluated the hot gas ingestion phenomena at higher temperatures and used a laser sheet to investigate the flow field. Hot gas ingestion levels were measured for the several forward nozzle splay configurations and with flow control/life improvement devices (LIDs) which reduced the hot gas ingestion. The test was conducted at full scale nozzle pressure ratios and inlet Mach numbers. Results are presented over a range of nozzle pressure ratios at a 10 kn headwind velocity. The Phase 2 program was conducted at exhaust nozzle temperatures up to 1460 R and utilized a sheet laser system for flow visualization of the model flow field in and out of ground effects. The results reported are for nozzle exhaust temperatures up to 1160 R and contain the compressor face pressure and temperature distortions, the total pressure recovery, the inlet temperature rise, and the environmental effects of the hot gas. The environmental effects include the ground plane contours, the model airframe heating, and the location of the ground flow separation.
Document ID
19910055938
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Johns, Albert L.
(NASA Lewis Research Center Cleveland, OH, United States)
Neiner, George
(NASA Lewis Research Center Cleveland, OH, United States)
Bencic, Timothy J.
(NASA Lewis Research Center Cleveland, OH, United States)
Flood, Joseph D.
(NASA Lewis Research Center Cleveland, OH, United States)
Amuedo, Kurt C.
(McDonnell Aircraft Co. Saint Louis, MO, United States)
Date Acquired
August 15, 2013
Publication Date
July 1, 1990
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 90-2268
Accession Number
91A40561
Distribution Limits
Public
Copyright
Other

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