NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
An iterative finite element-integral technique for predicting sound radiation from turbofan inlets in steady flightA new iterative solution technique for predicting the sound field radiated from a turbofan inlet in steady flight is presented. The sound field is divided into two regions: the sound field within and near the inlet which is computed using the finite element method and the radiation field beyond the inlet which is calculated using an integral solution technique. A continuous solution is obtained by matching the finite element and integral solutions at the interface between the two regions. The applicability of the iterative technique is demonstrated by comparison of experimental results with the theoretical results for several different inlet configurations with and without flow. These examples show that good agreement between experiment and theory is obtained within five iterations.
Document ID
19820034261
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Horowitz, S. J.
(Georgia Inst. of Tech. Atlanta, GA, United States)
Sigman, R. K.
(Georgia Inst. of Tech. Atlanta, GA, United States)
Zinn, B. T.
(Georgia Institute of Technology Atlanta, GA, United States)
Date Acquired
August 10, 2013
Publication Date
January 1, 1982
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA PAPER 82-0124
Meeting Information
Meeting: Aerospace Sciences Meeting
Location: Orlando, FL
Start Date: January 11, 1982
End Date: January 14, 1982
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
82A17796
Funding Number(s)
CONTRACT_GRANT: NSG-3036
Distribution Limits
Public
Copyright
Other

Available Downloads

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