Over-expansion effects on Mach 3.0 supersonic jet acoustics

Taku Nonomura, Kozo Fujii

Research output: Chapter in Book/Report/Conference proceedingConference contribution

12 Citations (Scopus)

Abstract

For the prediction of acoustic waves from rocket plume, over-expansion effects on Mach 3.0 supersonic jet acoustics are investigated with monotonically integrated large eddy simulation. In this study, ideally-expanded Mach number and designed Mach number are used to express the jet conditions. Three designed Mach number 3.0, 3.5 and 4.0 are chosen, while ideally-expanded Mach number is constant 3.0. Reynolds number is 100000 and coldjet condition is adopted to reduce computational costs. With regard to computation, the seventh order weighted compact non-linear scheme and the tenth order compact scheme are used for solving the jet-flow and near fields acoustics propagation, respectively. Computational results of Mach wave emissions of these three conditions are almost same. This result corresponds to that of relatively low Mach number supersonic which is reported by Tam(AIAA paper 2005-2938). Present results show that it can be applied to high Mach number supersonic jet. For the the prediction of acoustic waves from rocket plume, this results imply that rocket parameters could be reduced.

Original languageEnglish
Title of host publication14th AIAA/CEAS Aeroacoustics Conference (29th AIAA Aeroacoustics Conference)
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
ISBN (Print)9781563479397
DOIs
Publication statusPublished - 2008
Externally publishedYes

Publication series

Name14th AIAA/CEAS Aeroacoustics Conference (29th AIAA Aeroacoustics Conference)

ASJC Scopus subject areas

  • Engineering(all)

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