Hostname: page-component-78c5997874-lj6df Total loading time: 0 Render date: 2024-11-17T17:21:55.747Z Has data issue: false hasContentIssue false

NASA subsonic jet transport noise reduction research

Published online by Cambridge University Press:  04 July 2016

C. A. Powell
Affiliation:
NASA Langley Research Center
J. S. Preisser
Affiliation:
NASA Langley Research Center

Abstract

Although new jet transport aircraft in today’s fleet are considerably quieter than the first jet transports introduced about 40 years ago, airport community noise continues to be an important environmental issue. NASA’s Advanced Subsonic Transport (AST) Noise Reduction programme was begun in 1994 as a seven-year effort to develop technology to reduce jet transport noise 10dB relative to 1992 technology. This programme provides for reductions in engine source noise, improvements in nacelle acoustic treatments, reductions in the noise generated by the airframe, and improvements in the way aircraft are operated in the airport environs. These noise reduction efforts will terminate at the end of 2001 and it appears that the objective will be met. However, because of an anticipated 3-8% growth in passenger and cargo operations well into the 21st century and the slow introduction of the new noise reduction technology into the fleet, world aircraft noise impact will remain essentially constant until about 2020 to 2030 and thereafter begin to rise. Therefore, NASA has begun planning with the FAA, industry, universities and environmental interest groups in the USA for a new noise reduction initiative to provide technology for significant further reductions.

Type
Research Article
Copyright
Copyright © Royal Aeronautical Society 2000 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1. Saiyed, N., Mikkelsen, K. and Bridges, J. Acoustics and thrust of separate flow exhaust nozzles with mixing devices for high bypass-ratio engines. 6th AIAA/CEAS Aeroacoustics Conference, Lahaina, Hawaii. AIAA Paper 2000-1961, 2000.Google Scholar
2. Dunn, M, Tweed, J. and Farassat, F. The application of boundary integral equation method to the prediction of ducted fan engine noise. J Sound Vib, 1999, 227, (5), pp 10191048.Google Scholar
3. Watson, W. Three-dimensional nacelle aeroacoustics code with application to impedance eduction. 6th AIAA/CEAS Aeroacoustics Conference, Lahaina Hawaii, AIAA Paper 2000-1956, 2000.Google Scholar
4. Burdisso, R. and Smith, P. Control of inlet noise from turbofan engines using Herschel-Quincke waveguides. 6th AIAA/CEAS Aeroacoustics conference, Lahaina, Hawaii, AIAA Paper 2000-1994, 2000.Google Scholar
5. Macaraeg, M. Fundamental investigations of airframe noise, 4th AIAA/CEAS Aeroacoustics Conference, Toulouse, France, AIAA Paper-98-2224, 1998.Google Scholar