NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
A jet exhaust noise prediction procedure for inverted velocity profile coannular nozzlesAcoustic model tests have demonstrated that significant noise suppression can be obtained from inverted velocity profile coannular nozzles. An acoustic prediction procedure was developed for inverted velocity profile coannular nozzles that can be used to predict SPL spectra as a function of nozzle geometry and flow conditions. In the development of this prediction procedure, the noise spectrum at a given angle was decomposed into four noise components: a low frequency mixing noise component, a high frequency mixing noise component, an outer stream shock noise component, and an inner stream shock noise component. The physics of the inverted velocity flow field development was used to formulate noise generation models. Scaling laws for each noise component were defined based on these models. Comparisons of predictions from this procedure with experimental data were conducted to verify the prediction procedure.
Document ID
19790044951
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Larson, R. S.
(United Technologies Corp. Pratt and Whitney Aircraft Group, East Hartford, Conn., United States)
Date Acquired
August 9, 2013
Publication Date
March 1, 1979
Subject Category
Acoustics
Report/Patent Number
AIAA PAPER 79-0633
Meeting Information
Meeting: American Institute of Aeronautics and Astronautics, Aeroacoustics Conference
Location: Seattle, WA
Start Date: March 12, 1979
End Date: March 14, 1979
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
79A28964
Funding Number(s)
CONTRACT_GRANT: NAS3-20061
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.
No Preview Available