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Thrust performance of isolated 36-chute suppressor plug nozzles with and without ejectors at Mach numbers from 0 to 0.45Plug nozzles with chute-type noise suppressors were tested with and without ejector shrouds at free-stream Mach numbers from 0 to 0.45 and over a range of nozzle pressure ratios from 2 to 4. A 36-chute suppressor nozzle with an ejector had an efficiency of 94.6 percent at an assumed takeoff pressure ratio of 3.0 and a Mach number of 0.36. This represents only a 3.4 percent performance penalty when compared with the 98 percent efficiency obtained with a previously tested unsuppressed plug nozzle.
Document ID
19760003038
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Harrington, D. E. (NASA Lewis Research Center Cleveland, OH, United States)
Schloemer, J. J. (GE Co. Cincinnati, United States)
Skebe, S. A. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
October 1, 1975
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
E-8334
NASA-TM-X-3298
Accession Number
76N10126
Funding Number(s)
PROJECT: RTOP 505-11
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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