Mach number dependence on sound sources in high mach number turbulent mixing layer

Daiki Terakado; Taku Nonomura; Akira Oyama; Kozo Fujii

Mach number dependence on sound sources in high mach number turbulent mixing layer

Daiki Terakado, Taku Nonomura, Akira Oyama, Kozo Fujii

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

Abstract

The convective Mach number dependences of sound sources in a compressible mixing layer are investigated by direct numerical simulation. Characteristics of sound sources are analyzed using the source terms of the Lighthill equation. The acoustic waves become weaker with increasing the Mach number due to the weaker vortices by compressibility and the canceling out of the Reynolds stress term and the entropy term. Also, the smaller scale acoustic waves appears for M_c ≥ 1.5. The results suggest that those change in the characteristics of the sound sources are due to the appearance of shocklets for larger convective Mach number cases. Also, those cases show the higher turbulent Mach number over the wide range of flow field.

Original language	English
Title of host publication	22nd AIAA/CEAS Aeroacoustics Conference
Publisher	American Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)	9781624103865
Publication status	Published - 2016
Externally published	Yes
Event	22nd AIAA/CEAS Aeroacoustics Conference, 2016 - Lyon, France Duration: 2016 May 30 → 2016 Jun 1

Other

Other	22nd AIAA/CEAS Aeroacoustics Conference, 2016
Country/Territory	France
City	Lyon
Period	16/5/30 → 16/6/1

ASJC Scopus subject areas

Electrical and Electronic Engineering
Aerospace Engineering

Cite this

@inproceedings{46d4960ee0594992aa78612015bf7c8f,

title = "Mach number dependence on sound sources in high mach number turbulent mixing layer",

abstract = "The convective Mach number dependences of sound sources in a compressible mixing layer are investigated by direct numerical simulation. Characteristics of sound sources are analyzed using the source terms of the Lighthill equation. The acoustic waves become weaker with increasing the Mach number due to the weaker vortices by compressibility and the canceling out of the Reynolds stress term and the entropy term. Also, the smaller scale acoustic waves appears for Mc ≥ 1.5. The results suggest that those change in the characteristics of the sound sources are due to the appearance of shocklets for larger convective Mach number cases. Also, those cases show the higher turbulent Mach number over the wide range of flow field.",

author = "Daiki Terakado and Taku Nonomura and Akira Oyama and Kozo Fujii",

year = "2016",

language = "English",

isbn = "9781624103865",

booktitle = "22nd AIAA/CEAS Aeroacoustics Conference",

publisher = "American Institute of Aeronautics and Astronautics Inc, AIAA",

note = "22nd AIAA/CEAS Aeroacoustics Conference, 2016 ; Conference date: 30-05-2016 Through 01-06-2016",

}

TY - GEN

T1 - Mach number dependence on sound sources in high mach number turbulent mixing layer

AU - Terakado, Daiki

AU - Nonomura, Taku

AU - Oyama, Akira

AU - Fujii, Kozo

PY - 2016

Y1 - 2016

N2 - The convective Mach number dependences of sound sources in a compressible mixing layer are investigated by direct numerical simulation. Characteristics of sound sources are analyzed using the source terms of the Lighthill equation. The acoustic waves become weaker with increasing the Mach number due to the weaker vortices by compressibility and the canceling out of the Reynolds stress term and the entropy term. Also, the smaller scale acoustic waves appears for Mc ≥ 1.5. The results suggest that those change in the characteristics of the sound sources are due to the appearance of shocklets for larger convective Mach number cases. Also, those cases show the higher turbulent Mach number over the wide range of flow field.

AB - The convective Mach number dependences of sound sources in a compressible mixing layer are investigated by direct numerical simulation. Characteristics of sound sources are analyzed using the source terms of the Lighthill equation. The acoustic waves become weaker with increasing the Mach number due to the weaker vortices by compressibility and the canceling out of the Reynolds stress term and the entropy term. Also, the smaller scale acoustic waves appears for Mc ≥ 1.5. The results suggest that those change in the characteristics of the sound sources are due to the appearance of shocklets for larger convective Mach number cases. Also, those cases show the higher turbulent Mach number over the wide range of flow field.

UR - http://www.scopus.com/inward/record.url?scp=84982972099&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=84982972099&partnerID=8YFLogxK

M3 - Conference contribution

SN - 9781624103865

BT - 22nd AIAA/CEAS Aeroacoustics Conference

PB - American Institute of Aeronautics and Astronautics Inc, AIAA

T2 - 22nd AIAA/CEAS Aeroacoustics Conference, 2016

Y2 - 30 May 2016 through 1 June 2016

ER -

Mach number dependence on sound sources in high mach number turbulent mixing layer

Abstract

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ASJC Scopus subject areas

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