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An analysis of screech tone noise and its mode change of an axisymmetric supersonic jet using optimised compact schemes

Record type: Conference or Workshop Item (Paper)

The screech tone of an underexpanded jet is numerically calculated without any specific modeling for the screech tone itself. A fourth-order optimized compact scheme and fourthorder Runge-Kutta method are used to solve the 2D axisymmetric Euler equation. First, the centerline mean pressure distribution of jet Mach number 1.20 is calculated and compared with experimental and other numerical results. The agreement with other results means that present method can simulate the axisymmetric screech tone correctly. The pressure signal and its Fourier transform at upstream and downstream show the directivity pattern of the screech tone very clearly. Most importantly, we can simulate the axisymmetric mode change of the screech tone very precisely with the proposed method. Moreover, the numerical results show that the mode change pattern of the screech tone is almost same regardless of the nozzle lip thickness. It can be concluded that the basic phenomenon of screech tone including its frequency can be calculated and its mode change can be simulated with inviscid Euler equations but without any numerical modeling for the screech tone feedback loop.

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Citation

Lee, I.C., Kim, J.W. and Lee, D.J. (2004) An analysis of screech tone noise and its mode change of an axisymmetric supersonic jet using optimised compact schemes At 10th AIAA/CEAS Aeroacoustics Conference. 10 - 12 May 2004. , p. 2952.

More information

Published date: 2004
Venue - Dates: 10th AIAA/CEAS Aeroacoustics Conference, 2004-05-10 - 2004-05-12
Organisations: Aerodynamics & Flight Mechanics

Identifiers

Local EPrints ID: 23567
URI: http://eprints.soton.ac.uk/id/eprint/23567
ISBN: 1-56347-713-0
PURE UUID: 377c4f7f-4127-48ce-829d-359431447eba

Catalogue record

Date deposited: 06 Apr 2006
Last modified: 17 Jul 2017 16:17

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