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High-Temperature Effects on Aerodynamic and Acoustic Characteristics of a Rectangular Supersonic Jet
KTH, School of Engineering Sciences (SCI), Mechanics.
KTH, School of Engineering Sciences (SCI), Mechanics.
KTH, School of Engineering Sciences (SCI), Mechanics.ORCID iD: 0000-0001-7330-6965
2018 (English)In: AIAA/CEAS Aeroacoustics Conference, AIAA AVIATION Forum, 2018 / [ed] AIAA, 2018, article id 3303Conference paper, Published paper (Refereed)
Abstract [en]

Implicit large-eddy simulations (LES) are performed in this work to study the flow field and acous-tic characteristics of a rectangular supersonic jet. The focus is to investigate the high-temperatureeffects, i.e. when the jet total temperature is as high as 2100 K. Four cases with a jet temperatureratio(TR) of 1.0, 2.0, 4.0 and 7.0 are investigated. The rectangular nozzle selected for this study hasan aspect ratio of 2. The jets are overexpanded, with a series of shock cells in the jet core region.An artificial dissipation mechanism is used to damp the numerical oscillation and to represent theeffect of small-scale turbulence. The temperature-dependent thermal properties of air within thehigh-temperature regime are also considered by using the chemical equilibrium assumption. Thenumerical results show that the high temperature significantly increases the jet velocity and acousticMach number, although the jet Mach number is maintained roughly the same. Meanwhile, the lengthof the jet core region of the hot jet (TR = 7.0) is found to be reduced by around 30 %, compared tothe cold jet. The convection velocity and acoustic convection Mach number in the shear layer are alsoobserved to be increased when the jet temperature is high. The elevated acoustic convection Machnumber directly leads to a strong Mach wave radiation, and the crackle noise component has beenidentified by the pressure skewness and kurtosis factors. The Strouhal number of the screech tone isfound to be decreased slightly, and good agreements between the numerical results and the theoreticalanalysis are observed. Moreover, the sound pressure levels (SPL) associated with turbulent mixing,screech, Mach wave radiation, and Broadband shock associated noise are all found to be amplified indifferent levels for the hot jets. In the far field, the SPL is strongly increased by the high-temperatureeffect. Higher SPL is notably observed in the Mach wave radiation directions.

Place, publisher, year, edition, pages
2018. article id 3303
Keywords [en]
Large Eddy Simulation, Supersonic rectangular jets, Aeroacoustics, Temperature effects
National Category
Fluid Mechanics and Acoustics Aerospace Engineering
Research subject
Engineering Mechanics
Identifiers
URN: urn:nbn:se:kth:diva-235799DOI: 10.2514/6.2018-3303Scopus ID: 2-s2.0-85051292277ISBN: 978-1-62410-560-9 (electronic)OAI: oai:DiVA.org:kth-235799DiVA, id: diva2:1253471
Conference
AIAA/CEAS Aeroacoustics Conference, AIAA AVIATION Forum, (AIAA 2018-3303)
Note

QC 20181010

QC 20181017

Available from: 2018-10-04 Created: 2018-10-04 Last updated: 2018-10-17Bibliographically approved

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Publisher's full textScopushttps://doi.org/10.2514/6.2018-3303

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Chen, SongGojon, RomainMihaescu, Mihai

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