Experimental investigation of reynolds number effect on the aeroacoustics fields of a supersonic jet

Yuta Ozawa, Taku Nonomura, Akira Oyama, Makoto Yamamoto

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

1 Citation (Scopus)


The flow structure and near field acoustic profile of a supersonic jet at a Mach number of 2.0 and Reynolds numbers of 105 and 106 were investigated by particle imaging velocimetry, schlieren visualization and acoustic measurement using a microphone. The effect of the disturbance in the shear layer was also investigated. In the case of higher Reynolds number jet, the presence of disturbance does not significantly affect the flow and acoustic fields because the shear layer state has already been turbulent even without the disturbance. However, presence of disturbance significantly affects the flow and acoustic fields in the case of moderate Reynolds number jet (Re=105) because the initial condition of the shear layer without disturbance is laminar and disturbance promotes the turbulent transition which has the strong influence on flow and acoustic fields. The sound pressure level decreases with adding disturbance because the promoted turbulent shear layer is smoothly growing instead of rapid growth in the vicinity of the transition which leads to strong acoustic wave emission.

Original languageEnglish
Title of host publication25th AIAA/CEAS Aeroacoustics Conference, 2019
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624105883
Publication statusPublished - 2019
Externally publishedYes
Event25th AIAA/CEAS Aeroacoustics Conference, 2019 - Delft, Netherlands
Duration: 2019 May 202019 May 23

Publication series

Name25th AIAA/CEAS Aeroacoustics Conference, 2019


Conference25th AIAA/CEAS Aeroacoustics Conference, 2019

ASJC Scopus subject areas

  • Acoustics and Ultrasonics
  • Electrical and Electronic Engineering
  • Aerospace Engineering


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