NASA LogoNTRSNTRS - NASA Technical Reports ServerSearchmore_vertCollectionsAboutNewsHelpLogin Back to ResultsHot 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 ID19910011803Acquisition SourceLegacy CDMSDocument TypeConference PaperAuthorsJohns, 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 AcquiredSeptember 6, 2013Publication DateJuly 1, 1990Subject CategoryAerodynamicsReport/Patent NumberNAS 1.15:103258NASA-TM-103258E-5690AIAA PAPER 90-2268Meeting InformationMeeting: Joint Propulsion ConferenceLocation: Orlando, FLCountry: United StatesStart Date: July 16, 1990End Date: July 18, 1990Sponsors:AIAA,ASEE,ASME,SAEAccession Number91N21116Funding Number(s)PROJECT: RTOP 505-62-71Distribution LimitsPublicCopyrightWork of the US Gov. Public Use Permitted.Available DownloadsNameType19910011803.pdfSTIcloud_downloadcontent_copyvisibilityRelated RecordsThere are no records associated with this record.visibility_offNo Preview Available
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