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Hot gas ingestion test results of a two-poster vectored thrust concept with flow visualization in the NASA Lewis 9- x 15-foot low speed wind tunnelA 9.2 percent scale Short Takeoff and Vertical Landing (STOVL) hot gas ingestion model was designed and built by McDonnell Douglas Corporation (MCAIR) and tested in the Lewis Research Center 9 x 15 foot Low Speed Wind Tunnel (LSWT). Hot gas ingestion, the entrainment of heated engine exhaust into the inlet flow field, is a key development issure for advanced short takeoff and vertical landing aircraft. 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 model support system had four degrees of freedom - pitch, roll, yaw, and vertical height variation. The model support system also provided heated high-pressure air for nozzle flow and a suction system exhaust for inlet flow. The test was conducted at full scale nozzle pressure ratios and inlet Mach numbers. Test and data analysis results from Phase 2 and flow visualization from both Phase 1 and 2 are documented. A description of the model and facility modifications is also provided. Headwind velocity was varied from 10 to 23 kn. 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. These results will 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
19910011803
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.
(McDonnell-Douglas Corp. Saint Louis, MO., United States)
Amuedo, Kurt C.
(McDonnell-Douglas Corp. Saint Louis, MO., United States)
Strock, Thomas W.
(McDonnell-Douglas Corp. Saint Louis, MO., United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1990
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.15:103258
NASA-TM-103258
E-5690
AIAA PAPER 90-2268
Meeting Information
Meeting: Joint Propulsion Conference
Location: Orlando, FL
Country: United States
Start Date: July 16, 1990
End Date: July 18, 1990
Sponsors: AIAA, ASEE, ASME, SAE
Accession Number
91N21116
Funding Number(s)
PROJECT: RTOP 505-62-71
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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