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Aerodynamic and acoustic performance of ejectors for engine-under-the-wing conceptsSubsonic thrust augmentation, exhaust plume velocity contours and acoustic characteristics of a small-scale, 6-tube mixer nozzle with ejector were obtained with and without a wing. Thrust augmentation up to 30 percent was achieved. Aerodynamic results showed that at a given location, greater downstream velocities are obtained with an ejector than with the baseline nozzle. Ejectors reduce high frequency noise; however, low frequency noise amplification also occurs. Acoustic reflections off the wing increase the noise level to a ground observer. With an ejector, the acoustic benefits of forward velocity may be significantly reduced compared with the baseline nozzle.
Document ID
19740021272
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Vonglahn, U. (NASA Lewis Research Center Cleveland, OH, United States)
Goodykoontz, J. H. (NASA Lewis Research Center Cleveland, OH, United States)
Groesbeck, D. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
January 1, 1974
Subject Category
Aircraft
Report/Patent Number
NASA-TM-X-71587
E-8039
Meeting Information
Meeting: Aircraft Design, Flight Test and Operations Meeting
Location: Los Angeles
Start Date: August 12, 1974
End Date: August 14, 1974
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
74N29385
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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