Simulation of underexpanded supersonic jet flows with chemical reactions
To achieve a detailed understanding of underexpanded supersonic jet structures influenced by afterburning and other flow conditions, the underexpanded turbulent supersonic jet with and without combustions are investigated by computational fluid dynamics （CFD） method. A program based on a total varia...
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| Veröffentlicht in: | Chinese journal of aeronautics 2014-06, Vol.27 (3), p.505-513 |
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| container_title | Chinese journal of aeronautics |
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| creator | Fu, Debin Yu, Yong Niu, Qinglin |
| description | To achieve a detailed understanding of underexpanded supersonic jet structures influenced by afterburning and other flow conditions, the underexpanded turbulent supersonic jet with and without combustions are investigated by computational fluid dynamics （CFD） method. A program based on a total variation diminishing （TVD） methodology capable of predicting complex shocks is created to solve the axisymmetric expanded Navie~Stokes equations containing transport equations of species. The finite-rate ratio model is employed to handle species sources in chemical reactions. CFD solutions indicate that the structure of underexpanded jet is typically influenced by the pressure ratio and afterburning. The shock reflection distance and maximum value of Mach number in the first shock cell increase with pressure ratio. Chemical reactions for the rocket exhaust mostly exist in the mixing layer of supersonic jet flows. This tends to reduce the intensity of shocks existing in the jet, responding to the variation of thermal parameters. |
| doi_str_mv | 10.1016/j.cja.2014.04.003 |
| format | Article |
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A program based on a total variation diminishing （TVD） methodology capable of predicting complex shocks is created to solve the axisymmetric expanded Navie~Stokes equations containing transport equations of species. The finite-rate ratio model is employed to handle species sources in chemical reactions. CFD solutions indicate that the structure of underexpanded jet is typically influenced by the pressure ratio and afterburning. The shock reflection distance and maximum value of Mach number in the first shock cell increase with pressure ratio. Chemical reactions for the rocket exhaust mostly exist in the mixing layer of supersonic jet flows. This tends to reduce the intensity of shocks existing in the jet, responding to the variation of thermal parameters.</description><subject>Afterburning</subject><subject>Chemical reactions</subject><subject>Combustion</subject><subject>Computational fluid dynamics</subject><subject>Finite-rate model</subject><subject>Mathematical models</subject><subject>Navier-Stokes equations</subject><subject>Numerical simulation</subject><subject>Pressure ratio</subject><subject>Stokes方程</subject><subject>Supersonic aircraft</subject><subject>Supersonic jet flow</subject><subject>TVD method</subject><subject>Underexpanded jet</subject><subject>仿真</subject><subject>化学反应流</subject><subject>总变差减小</subject><subject>欠膨胀射流</subject><subject>热物性参数</subject><subject>计算流体动力学</subject><subject>超音速射流</subject><issn>1000-9361</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2014</creationdate><recordtype>article</recordtype><recordid>eNp9UEFOwzAQzAEkSuEB3MKNS4Mdp3EsTqgCilSJA3C2nPW6dZTErZ1Q-D2uWnFEGmmk1czO7iTJDSUZJbS8bzJoVJYTWmQkgrCzZEIJITPBSnqRXIbQxKHglEyS5bvtxlYN1vWpM-nYa_T4vVWRdRrGLfrgegtpg0NqWrcP6d4OmxQ22FlQbepRwcEcrpJzo9qA1yeeJp_PTx-L5Wz19vK6eFzNoGD5MCs1F5UWBTOc1rkQTJjaiAqAFYLkwKEC5EYTDqIsEXReQ4GqqvPK8LkBzabJ3XHv1rvdiGGQnQ2Abat6dGOQtCwJmccaeJTSoxS8C8GjkVtvO-V_JCXy0JRsZGxKHpqSJIKw6Hk4ejD-8GXRywAWe0BtPcIgtbP_um9PiRvXr3e2X_9FxpMon-cF-wX-IH-I</recordid><startdate>20140601</startdate><enddate>20140601</enddate><creator>Fu, Debin</creator><creator>Yu, Yong</creator><creator>Niu, Qinglin</creator><general>Elsevier Ltd</general><scope>2RA</scope><scope>92L</scope><scope>CQIGP</scope><scope>W92</scope><scope>~WA</scope><scope>6I.</scope><scope>AAFTH</scope><scope>AAYXX</scope><scope>CITATION</scope><scope>7TB</scope><scope>8FD</scope><scope>FR3</scope><scope>H8D</scope><scope>L7M</scope></search><sort><creationdate>20140601</creationdate><title>Simulation of underexpanded supersonic jet flows with chemical reactions</title><author>Fu, Debin ; Yu, Yong ; Niu, Qinglin</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-c432t-6d798d943f71b29939fbf98cc34902c7c8ce7fd07c966ecd2bc4ea8b28f75fcd3</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2014</creationdate><topic>Afterburning</topic><topic>Chemical reactions</topic><topic>Combustion</topic><topic>Computational fluid dynamics</topic><topic>Finite-rate model</topic><topic>Mathematical models</topic><topic>Navier-Stokes equations</topic><topic>Numerical simulation</topic><topic>Pressure ratio</topic><topic>Stokes方程</topic><topic>Supersonic aircraft</topic><topic>Supersonic jet flow</topic><topic>TVD method</topic><topic>Underexpanded jet</topic><topic>仿真</topic><topic>化学反应流</topic><topic>总变差减小</topic><topic>欠膨胀射流</topic><topic>热物性参数</topic><topic>计算流体动力学</topic><topic>超音速射流</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Fu, Debin</creatorcontrib><creatorcontrib>Yu, Yong</creatorcontrib><creatorcontrib>Niu, Qinglin</creatorcontrib><collection>中文科技期刊数据库</collection><collection>中文科技期刊数据库-CALIS站点</collection><collection>中文科技期刊数据库-7.0平台</collection><collection>中文科技期刊数据库-工程技术</collection><collection>中文科技期刊数据库- 镜像站点</collection><collection>ScienceDirect Open Access Titles</collection><collection>Elsevier:ScienceDirect:Open Access</collection><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>Chinese journal of aeronautics</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>Fu, Debin</au><au>Yu, Yong</au><au>Niu, Qinglin</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Simulation of underexpanded supersonic jet flows with chemical reactions</atitle><jtitle>Chinese journal of aeronautics</jtitle><addtitle>Chinese Journal of Aeronautics</addtitle><date>2014-06-01</date><risdate>2014</risdate><volume>27</volume><issue>3</issue><spage>505</spage><epage>513</epage><pages>505-513</pages><issn>1000-9361</issn><abstract>To achieve a detailed understanding of underexpanded supersonic jet structures influenced by afterburning and other flow conditions, the underexpanded turbulent supersonic jet with and without combustions are investigated by computational fluid dynamics （CFD） method. A program based on a total variation diminishing （TVD） methodology capable of predicting complex shocks is created to solve the axisymmetric expanded Navie~Stokes equations containing transport equations of species. The finite-rate ratio model is employed to handle species sources in chemical reactions. CFD solutions indicate that the structure of underexpanded jet is typically influenced by the pressure ratio and afterburning. The shock reflection distance and maximum value of Mach number in the first shock cell increase with pressure ratio. Chemical reactions for the rocket exhaust mostly exist in the mixing layer of supersonic jet flows. This tends to reduce the intensity of shocks existing in the jet, responding to the variation of thermal parameters.</abstract><pub>Elsevier Ltd</pub><doi>10.1016/j.cja.2014.04.003</doi><tpages>9</tpages><oa>free_for_read</oa></addata></record> |
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| identifier | ISSN: 1000-9361 |
| ispartof | Chinese journal of aeronautics, 2014-06, Vol.27 (3), p.505-513 |
| issn | 1000-9361 |
| language | eng |
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| source | ScienceDirect Journals (5 years ago - present); EZB-FREE-00999 freely available EZB journals |
| subjects | Afterburning Chemical reactions Combustion Computational fluid dynamics Finite-rate model Mathematical models Navier-Stokes equations Numerical simulation Pressure ratio Stokes方程 Supersonic aircraft Supersonic jet flow TVD method Underexpanded jet 仿真 化学反应流 总变差减小 欠膨胀射流 热物性参数 计算流体动力学 超音速射流 |
| title | Simulation of underexpanded supersonic jet flows with chemical reactions |
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