Noise radiated by a non-isothermal, temporal mixing layer. Part I: Direct computation and prediction using compressible DNS

Fortuné, Véronique; Lamballais, Éric; Gervais, Yves

doi:10.1007/s00162-004-0114-8

Cited by 41 publications

(25 citation statements)

References 44 publications

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“…A two-dimensional mixing layer is considered to investigate the sound field [4] induced by vortex motions (i.e. pairing, co-rotating, and merging) [9].…”

Section: Mixing Layer Noisementioning

confidence: 99%

Linearized perturbed compressible equations for low Mach number aeroacoustics

Seo

Moon

2006

Journal of Computational Physics

144

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“…A two-dimensional mixing layer is considered to investigate the sound field [4] induced by vortex motions (i.e. pairing, co-rotating, and merging) [9].…”

Section: Mixing Layer Noisementioning

confidence: 99%

Linearized perturbed compressible equations for low Mach number aeroacoustics

Seo

Moon

2006

Journal of Computational Physics

144

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“…The approach consisting in computing jet noise directly from the compressible Navier-Stokes equations has also reached maturity, see the review papers by Colonius & Lele, 37 Bailly & Bogey 38 and Wang et al, 39 as well as the most recent studies of the present authors on isothermal jets. [32][33][34][40][41][42] This approach has been applied to non-isothermal free shear flows, such as mixing layers by Fortuné et al 43 and Sharma & Lele, 44 axisymmetric jets by Lesshafft et al 45 and round jets by Bodony & Lele, 46 for example. The results were in general consistent with experimental observations, but notable discrepancies were also recognized.…”

Section: Introductionmentioning

confidence: 99%

Numerical investigation of temperature effects on properties of subsonic turbulent jets

Bogey

Marsden

2013

19th AIAA/CEAS Aeroacoustics Conference

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The influence of temperature on the flow and acoustic fields of high subsonic jets is investigated by computing one isothermal and three hot circular jets using large-eddy simulation. The jets have an identical velocity yielding a Mach number M = uj/ca = 0.9, and diameter-based Reynolds numbers ReD = ujD/νj between 2.5 × 10 4 and 10 5 , where subscripts j and a denote inflow and ambient conditions. They are characterized by similar nozzle-exit boundary-layer parameters, including 9% of peak turbulence intensity. The isothermal jet is at a temperature Tj = Ta and at ReD = 10 5 . The next two jets are at Tj = 1.5Ta and Tj = 2.25Ta, and have the same diameter as the isothermal jet, leading to ReD = 5 × 10 4 and ReD = 2.5 × 10 4 , respectively. The last jet is also at Tj = 1.5Ta, but its diameter is doubled in order to obtain ReD = 10 5 . In all cases, with rising temperature, the jets develop more rapidly with higher turbulence levels, and generate more noise at low frequencies and less noise at high frequencies in the flow direction, in agreement with corresponding measurements. The variations of the shear-layer properties and of the farfield pressure levels with Tj are however strongly dependent on the Reynolds number. For the jets at a constant diameter, due to the decrease in ReD, the mixing layers spread more quickly with higher velocity fluctuations and length scales, and the overall sound intensity increases. For the hot jet at ReD = 10 5 , on the contrary, the flow field downstream of the nozzle does not change significantly with respect to the isothermal case, and a noise reduction is found as observed experimentally for high Reynolds number jets at M > 0.7.

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“…In order to trigger transition, a velocity perturbation is added to this mean profile (Fortune et al [2004], Fu and Li [2006]). The fluctuating velocity field has an energy spectrum that follows eqn 4.3.…”

Section: )mentioning

confidence: 99%

Hybrid LES of Detonations in Reacting Multi-Phase Mixtures

Menon¹,

Génin²

2009

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REPORT DOCUMENTATION PAGEThe public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing the burden, to Department of Defense, Washington Headquarters Services, Directorate for Information Operations and Reports (0704-0188), 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid 0MB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. REPORT DATE (DD-MM-YYYY) 28-02-2009 2. REPORT TYPE Final Report DATES COVERED {From -To)December 1 PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES)School of Aerospace Engineering Georgia Institute of Technology Atlanta, GA 30332 PERFORMING ORGANIZATION REPORT NUMBERCCL-TR-2009-02-1 SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES)AFOSR/NL 4015 Wilson Blvd ? Arlington, VA 22203 Dr. Fariba Fahroo SPONSOR/MONITORS ACRONYM(S)AFOSR/NM SPONSOR/MONITORS REPORT NUMBER(S) DISTRIBUTION/AVAILABILITY STATEMENTUnlimited, Unclassified SUPPLEMENTARY NOTES ABSTRACTA Large-Eddy Simulation (LES) methodology adapted to the resolution of high Reynolds number turbulent flows in supersonic conditions was proposed and developed. A novel numerical scheme was designed, that switches from a low-dissipation central scheme for turbulence resolution to a flux difference splitting scheme in regions of discontinuities. A state-of-the-art closure model was extended in order to take compressibility effects and the action of shock / turbulence interaction into account. The proposed method was validated and employed for the study of shock / turbulent shear layer interaction as a mixing-augmentation technique, and highlighted the efficiency in mixing improvement after the interaction, but also the limited spatial extent of this turbulent enhancement. A second study focused on the injection of a sonic jet normally to a supersonic crossflow. The validity of the simulation was assessed by comparison with experimental data, and the dynamics of the interaction was examined. The sources of vortical structures were identified, with a particular emphasis on the impact of the flow speed onto the vortical evolution. It is shown that the developed hybrid methodology permits a capture of shock / turbulence interactions in direct simulations that agrees well with other reference simulations, and that the LES methodology effectively reproduces the turbulence evolution and physical phenomena involved in the interaction. This numerical approach is then employed to study a problem of practical importance in high-speed mixing. The inter...

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Noise radiated by a non-isothermal, temporal mixing layer. Part I: Direct computation and prediction using compressible DNS

Cited by 41 publications

References 44 publications

Linearized perturbed compressible equations for low Mach number aeroacoustics

Linearized perturbed compressible equations for low Mach number aeroacoustics

Numerical investigation of temperature effects on properties of subsonic turbulent jets

Hybrid LES of Detonations in Reacting Multi-Phase Mixtures

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