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Mixer nozzle aeroacoustic characteristics for the energy efficient engineAeroacoustic tests are conducted on scale model mixer nozzle configurations, a separate flow nozzle, and a baseline conical nozzle in an anechoic chamber free-jet facility to investigate exhaust system designs. Far-field acoustic data and exhaust jet plume aerodynamic data are obtained for various combinations of exhaust jet velocity and simulated flight speed, with corrected microphone data at a constant 12.2 m arc distance, and scaled acoustic data at a sideline distance of 457 m. It is found that jet plume aerodynamic and acoustic characteristics of lobed mixer exhaust systems are similar to those of a conical nozzle operating at the same specific thrust, although differences occur at high frequencies, where the sound pressure level of the mixer nozzle is 1-5 dB higher than that of a conical nozzle. In addition, no direct correlation is found between exit plane turbulence levels and plume development or acoustic characteristics for mixer exhaust configurations.
Document ID
19810064235
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Gliebe, P. R.
(General Electric Co. Cincinnati, OH, United States)
Sandusky, G. T.
(General Electric Co., Aircraft Engine Group, Cincinnati OH, United States)
Chamberlin, R.
(NASA Lewis Research Center Transport Propulsion Office, Cleveland, OH, United States)
Date Acquired
August 11, 2013
Publication Date
October 1, 1981
Subject Category
Acoustics
Report/Patent Number
AIAA PAPER 81-1994
Meeting Information
Meeting: Aeroacoustics Conference
Location: Palo Alto, CA
Start Date: October 5, 1981
End Date: October 7, 1981
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
81A48639
Distribution Limits
Public
Copyright
Other

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