Large-Eddy Simulation of Supersonic Round Jets: Effects of Reynolds and Mach Numbers
Large-eddy simulations of supersonic turbulent jets are performed for Reynolds numbers of Re
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| creator | Bellan, Josette |
| description | Large-eddy simulations of supersonic turbulent jets are performed for Reynolds numbers of Re |
| doi_str_mv | 10.2514/1.J054548 |
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The subgrid terms in large-eddy simulations are modeled using a combination of the dynamic Smagorinsky (“General Circulation Experiments with the Primitive Equations. Part I, Basic Experiments,” Monthly Weather Review, Vol. 54, No. 1, 1963, pp. 99–164) and Yoshizawa (“Statistical Theory for Compressible Turbulent Shear Flows, with the Application to Subgrid Modelling,” Physics of Fluids, Vol. 54, No. 1, 1986, pp. 2152–2164) models. Simulations are performed for supersonic jets having Reynolds numbers of 1500, 3700, and 7900, and Mach numbers of 1.4 and 2.1. Two of the simulations are validated with experimental data. The Reynolds number value is observed to play a role in the transition to turbulence but, once transition is achieved, it has a subdued effect above a threshold value; that is, as seen experimentally for supersonic flows, a similarity is found here. This similarity occurs for Reynolds number values that are relatively small compared to those typical of the fully turbulent regime. The turbulent structures in the transition region are more coherent, and the potential core is longer when the Mach number is larger, which leads to a slower downstream velocity decay. The root-mean-square velocities are biased in the axial direction, as expected. In the fully turbulent regions, the computed Reynolds stress is higher for a larger-Mach-number jet. Peak pressure fluctuations occur at about half a jet diameter, radially away from the centerline of the jet, and this location is independent of both the Reynolds number and Mach number values. The pressure–velocity correlations and the turbulent kinetic energy profiles are investigated along the centerline and radial directions, and it is found that the peak turbulent kinetic energy occurs at the same location as the maximum pressure fluctuations.</description><identifier>ISSN: 0001-1452</identifier><identifier>EISSN: 1533-385X</identifier><identifier>DOI: 10.2514/1.J054548</identifier><language>eng</language><publisher>Virginia: American Institute of Aeronautics and Astronautics</publisher><subject>Compressibility ; Computational fluid dynamics ; Decay rate ; Fluid flow ; Kinetic energy ; Large eddy simulation ; Mach number ; Peak pressure ; Primitive equations ; Reynolds number ; Reynolds stress ; Shear flow ; Similarity ; Simulation ; Supersonic flow ; Turbulence ; Turbulent flow ; Turbulent jets ; Vortices ; Weather</subject><ispartof>AIAA journal, 2016-05, Vol.54 (5), p.1482-1498</ispartof><rights>Copyright © 2015 by the American Institute of Aeronautics and Astronautics, Inc. The U.S. Government has a royalty-free license to exercise all rights under the copyright claimed herein for Governmental purposes. All other rights are reserved by the copyright owner. Copies of this paper may be made for personal or internal use, on condition that the copier pay the $10.00 per-copy fee to the Copyright Clearance Center, Inc., 222 Rosewood Drive, Danvers, MA 01923; include the code and $10.00 in correspondence with the CCC.</rights><rights>Copyright © 2015 by the American Institute of Aeronautics and Astronautics, Inc. The U.S. Government has a royalty-free license to exercise all rights under the copyright claimed herein for Governmental purposes. All other rights are reserved by the copyright owner. Copies of this paper may be made for personal or internal use, on condition that the copier pay the $10.00 per-copy fee to the Copyright Clearance Center, Inc., 222 Rosewood Drive, Danvers, MA 01923; include the code 1533-385X/15 and $10.00 in correspondence with the CCC.</rights><rights>Copyright © 2015 by the American Institute of Aeronautics and Astronautics, Inc. The U.S. Government has a royalty-free license to exercise all rights under the copyright claimed herein for Governmental purposes. All other rights are reserved by the copyright owner. Copies of this paper may be made for personal or internal use, on condition that the copier pay the $10.00 per-copy fee to the Copyright Clearance Center, Inc., 222 Rosewood Drive, Danvers, MA 01923; include the code 1533-385X/15 and $10.00 in correspondence with the CCC.</rights><lds50>peer_reviewed</lds50><woscitedreferencessubscribed>false</woscitedreferencessubscribed><citedby>FETCH-LOGICAL-a349t-68d9055aa8543ef890f3c7feef99a7458709f79087dfa74fc849c6cefa4629283</citedby><cites>FETCH-LOGICAL-a349t-68d9055aa8543ef890f3c7feef99a7458709f79087dfa74fc849c6cefa4629283</cites></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><link.rule.ids>314,780,784,27924,27925</link.rule.ids></links><search><creatorcontrib>Bellan, Josette</creatorcontrib><title>Large-Eddy Simulation of Supersonic Round Jets: Effects of Reynolds and Mach Numbers</title><title>AIAA journal</title><description>Large-eddy simulations of supersonic turbulent jets are performed for Reynolds numbers of Re<10,000 for the purpose of understanding the effects of Reynolds numbers and the Mach number M. The subgrid terms in large-eddy simulations are modeled using a combination of the dynamic Smagorinsky (“General Circulation Experiments with the Primitive Equations. Part I, Basic Experiments,” Monthly Weather Review, Vol. 54, No. 1, 1963, pp. 99–164) and Yoshizawa (“Statistical Theory for Compressible Turbulent Shear Flows, with the Application to Subgrid Modelling,” Physics of Fluids, Vol. 54, No. 1, 1986, pp. 2152–2164) models. Simulations are performed for supersonic jets having Reynolds numbers of 1500, 3700, and 7900, and Mach numbers of 1.4 and 2.1. Two of the simulations are validated with experimental data. The Reynolds number value is observed to play a role in the transition to turbulence but, once transition is achieved, it has a subdued effect above a threshold value; that is, as seen experimentally for supersonic flows, a similarity is found here. This similarity occurs for Reynolds number values that are relatively small compared to those typical of the fully turbulent regime. The turbulent structures in the transition region are more coherent, and the potential core is longer when the Mach number is larger, which leads to a slower downstream velocity decay. The root-mean-square velocities are biased in the axial direction, as expected. In the fully turbulent regions, the computed Reynolds stress is higher for a larger-Mach-number jet. Peak pressure fluctuations occur at about half a jet diameter, radially away from the centerline of the jet, and this location is independent of both the Reynolds number and Mach number values. The pressure–velocity correlations and the turbulent kinetic energy profiles are investigated along the centerline and radial directions, and it is found that the peak turbulent kinetic energy occurs at the same location as the maximum pressure fluctuations.</description><subject>Compressibility</subject><subject>Computational fluid dynamics</subject><subject>Decay rate</subject><subject>Fluid flow</subject><subject>Kinetic energy</subject><subject>Large eddy simulation</subject><subject>Mach number</subject><subject>Peak pressure</subject><subject>Primitive equations</subject><subject>Reynolds number</subject><subject>Reynolds stress</subject><subject>Shear flow</subject><subject>Similarity</subject><subject>Simulation</subject><subject>Supersonic flow</subject><subject>Turbulence</subject><subject>Turbulent flow</subject><subject>Turbulent jets</subject><subject>Vortices</subject><subject>Weather</subject><issn>0001-1452</issn><issn>1533-385X</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2016</creationdate><recordtype>article</recordtype><recordid>eNp90U1LAzEQBuAgCtbqwX8QEEQPW_O5m3iTUj9KVWgreAsxm-jK7qYmu4f-e1Pagyh4GoZ5Zhh4ATjFaEQ4Zld4NEWccSb2wABzSjMq-Os-GCCEcIYZJ4fgKMbP1JFC4AFYznR4t9mkLNdwUTV9rbvKt9A7uOhXNkTfVgbOfd-WcGq7eA0nzlnTxY2Y23Xr6zJCnaaP2nzAp755S0vH4MDpOtqTXR2Cl9vJcnyfzZ7vHsY3s0xTJrssF6VEnGstOKPWCYkcNYWz1kmpC8ZFgaQrJBJF6VLvjGDS5MY6zXIiiaBDcLG9uwr-q7exU00Vja1r3VrfR4WFYJhIyYtEz37RT9-HNn2nCJOYiJxL8Z_CIs-RoEVOk7rcKhN8jME6tQpVo8NaYaQ2KSisdikke761utL6x7U_8BvvC4Ko</recordid><startdate>20160501</startdate><enddate>20160501</enddate><creator>Bellan, Josette</creator><general>American Institute of Aeronautics and Astronautics</general><scope>AAYXX</scope><scope>CITATION</scope><scope>7TB</scope><scope>8FD</scope><scope>FR3</scope><scope>H8D</scope><scope>L7M</scope></search><sort><creationdate>20160501</creationdate><title>Large-Eddy Simulation of Supersonic Round Jets: Effects of Reynolds and Mach Numbers</title><author>Bellan, Josette</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-a349t-68d9055aa8543ef890f3c7feef99a7458709f79087dfa74fc849c6cefa4629283</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2016</creationdate><topic>Compressibility</topic><topic>Computational fluid dynamics</topic><topic>Decay rate</topic><topic>Fluid flow</topic><topic>Kinetic energy</topic><topic>Large eddy simulation</topic><topic>Mach number</topic><topic>Peak pressure</topic><topic>Primitive equations</topic><topic>Reynolds number</topic><topic>Reynolds stress</topic><topic>Shear flow</topic><topic>Similarity</topic><topic>Simulation</topic><topic>Supersonic flow</topic><topic>Turbulence</topic><topic>Turbulent flow</topic><topic>Turbulent jets</topic><topic>Vortices</topic><topic>Weather</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Bellan, Josette</creatorcontrib><collection>CrossRef</collection><collection>Mechanical & Transportation Engineering Abstracts</collection><collection>Technology Research Database</collection><collection>Engineering Research Database</collection><collection>Aerospace Database</collection><collection>Advanced Technologies Database with Aerospace</collection><jtitle>AIAA journal</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>Bellan, Josette</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Large-Eddy Simulation of Supersonic Round Jets: Effects of Reynolds and Mach Numbers</atitle><jtitle>AIAA journal</jtitle><date>2016-05-01</date><risdate>2016</risdate><volume>54</volume><issue>5</issue><spage>1482</spage><epage>1498</epage><pages>1482-1498</pages><issn>0001-1452</issn><eissn>1533-385X</eissn><abstract>Large-eddy simulations of supersonic turbulent jets are performed for Reynolds numbers of Re<10,000 for the purpose of understanding the effects of Reynolds numbers and the Mach number M. The subgrid terms in large-eddy simulations are modeled using a combination of the dynamic Smagorinsky (“General Circulation Experiments with the Primitive Equations. Part I, Basic Experiments,” Monthly Weather Review, Vol. 54, No. 1, 1963, pp. 99–164) and Yoshizawa (“Statistical Theory for Compressible Turbulent Shear Flows, with the Application to Subgrid Modelling,” Physics of Fluids, Vol. 54, No. 1, 1986, pp. 2152–2164) models. Simulations are performed for supersonic jets having Reynolds numbers of 1500, 3700, and 7900, and Mach numbers of 1.4 and 2.1. Two of the simulations are validated with experimental data. The Reynolds number value is observed to play a role in the transition to turbulence but, once transition is achieved, it has a subdued effect above a threshold value; that is, as seen experimentally for supersonic flows, a similarity is found here. This similarity occurs for Reynolds number values that are relatively small compared to those typical of the fully turbulent regime. The turbulent structures in the transition region are more coherent, and the potential core is longer when the Mach number is larger, which leads to a slower downstream velocity decay. The root-mean-square velocities are biased in the axial direction, as expected. In the fully turbulent regions, the computed Reynolds stress is higher for a larger-Mach-number jet. Peak pressure fluctuations occur at about half a jet diameter, radially away from the centerline of the jet, and this location is independent of both the Reynolds number and Mach number values. The pressure–velocity correlations and the turbulent kinetic energy profiles are investigated along the centerline and radial directions, and it is found that the peak turbulent kinetic energy occurs at the same location as the maximum pressure fluctuations.</abstract><cop>Virginia</cop><pub>American Institute of Aeronautics and Astronautics</pub><doi>10.2514/1.J054548</doi><tpages>17</tpages></addata></record> |
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| subjects | Compressibility Computational fluid dynamics Decay rate Fluid flow Kinetic energy Large eddy simulation Mach number Peak pressure Primitive equations Reynolds number Reynolds stress Shear flow Similarity Simulation Supersonic flow Turbulence Turbulent flow Turbulent jets Vortices Weather |
| title | Large-Eddy Simulation of Supersonic Round Jets: Effects of Reynolds and Mach Numbers |
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