Numerical study of n-wave propagation using optimized compact finite difference schemes
Numerical study of n-wave propagation using optimized compact finite difference schemes
Among the aircraft noise sources, the fan is a dominant one in the high-bypass engine, especially during takeoff and landing. The fan noise can be classified into three types: blade passage frequency (BPF) tonal noise, multiple pure tonal (MPT) noise, and broadband noise. MPT noise levels can exceed the BPF tonal noise during takeoff and landing because shock waves are generated at the rotor tip in the today’s high-bypass engine when the revolutions per minute of the engine shaft is increased to get maximum thrust. Hawkings analyzed the shock wave coalescence by using one dimensional saw-toothed shock models. His analysis describes how an initial nonuniform wave train evolves to become increasingly irregular with distance. However, this type of analysis cannot be directly related to the irregularities in the fan geometry.
316-319
Shim, I.B.
48d54dd5-f0bb-4a98-9c71-fdbf1be7ab0d
Kim, J.W.
fedabfc6-312c-40fd-b0c1-7b4a3ca80987
Lee, D.J.
07e9aeba-8cdd-4476-bd03-b936bc2ca8c1
2003
Shim, I.B.
48d54dd5-f0bb-4a98-9c71-fdbf1be7ab0d
Kim, J.W.
fedabfc6-312c-40fd-b0c1-7b4a3ca80987
Lee, D.J.
07e9aeba-8cdd-4476-bd03-b936bc2ca8c1
Shim, I.B., Kim, J.W. and Lee, D.J.
(2003)
Numerical study of n-wave propagation using optimized compact finite difference schemes.
AIAA Journal, 41 (2), .
Abstract
Among the aircraft noise sources, the fan is a dominant one in the high-bypass engine, especially during takeoff and landing. The fan noise can be classified into three types: blade passage frequency (BPF) tonal noise, multiple pure tonal (MPT) noise, and broadband noise. MPT noise levels can exceed the BPF tonal noise during takeoff and landing because shock waves are generated at the rotor tip in the today’s high-bypass engine when the revolutions per minute of the engine shaft is increased to get maximum thrust. Hawkings analyzed the shock wave coalescence by using one dimensional saw-toothed shock models. His analysis describes how an initial nonuniform wave train evolves to become increasingly irregular with distance. However, this type of analysis cannot be directly related to the irregularities in the fan geometry.
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Published date: 2003
Organisations:
Aerodynamics & Flight Mechanics
Identifiers
Local EPrints ID: 23047
URI: http://eprints.soton.ac.uk/id/eprint/23047
ISSN: 0001-1452
PURE UUID: d419c962-e2ad-4416-b86e-fb89ff2fbe68
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Date deposited: 24 Mar 2006
Last modified: 16 Mar 2024 03:42
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Author:
I.B. Shim
Author:
D.J. Lee
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