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Gen 2.0 Mixer/Ejector Nozzle Test at LSAF June 1995 to July 1996Testing of the HSCT Generation 2.0 nozzle model hardware was conducted at the Boeing Low Speed Aeroacoustic Facility, LSAF. Concurrent measurements of noise and thrust were made at critical takeoff design conditions for a variety of mixer/ejector model hardware. Design variables such as suppressor area ratio, mixer area ratio, liner type and thickness, ejector length, lobe penetration, and mixer chute shape were tested. Parallel testing was conducted at G.E.'s Cell 41 acoustic free jet facility to augment the LSAF test. The results from the Gen 2.0 testing are being used to help shape the current nozzle baseline configuration and guide the efforts in the upcoming Generation 2.5 and 3.0 nozzle tests. The Gen 2.0 results have been included in the total airplane system studies conducted at MDC and Boeing to provide updated noise and thrust performance estimates.
Document ID
20050080701
Acquisition Source
Headquarters
Document Type
Contractor Report (CR)
Authors
Arney, L. D. (Boeing Commercial Airplane Co. Seattle, WA, United States)
Sandquist, D. L. (Boeing Commercial Airplane Co. Seattle, WA, United States)
Forsyth, D. W. (Boeing Commercial Airplane Co. Seattle, WA, United States)
Lidstone, G. L. (Boeing Commercial Airplane Co. Seattle, WA, United States)
Long-Davis, Mary Jo (NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
September 7, 2013
Publication Date
February 1, 2005
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
E-14804
NASA/CR-2005-213334
Funding Number(s)
WBS: WBS 22-714-09-46
CONTRACT_GRANT: NAS3-27235
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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