Direct numerical simulation of transition in a sharp cone boundary layer at Mach 6: fundamental breakdown
Direct numerical simulations (DNS) were performed to investigate the laminar–turbulent transition in a boundary layer on a sharp cone with an isothermal wall at Mach 6 and at zero angle of attack. The motivation for this research is to make a contribution towards understanding the nonlinear stages o...
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| Veröffentlicht in: | Journal of fluid mechanics 2015-04, Vol.768, p.175-218 |
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| description | Direct numerical simulations (DNS) were performed to investigate the laminar–turbulent transition in a boundary layer on a sharp cone with an isothermal wall at Mach 6 and at zero angle of attack. The motivation for this research is to make a contribution towards understanding the nonlinear stages of transition and the final breakdown to turbulence in hypersonic boundary layers. In particular, the role of second-mode fundamental resonance, or (K-type) breakdown, is investigated using high-resolution ‘controlled’ transition simulations. The simulations were carried out for the laboratory conditions of the hypersonic transition experiments conducted at Purdue University. First, several low-resolution simulations were carried out to explore the parameter space for fundamental resonance in order to identify the cases that result in strong nonlinear interactions. Subsequently, based on the results from this study, a set of highly resolved simulations that proceed deep into the turbulent breakdown region have been performed. The nonlinear interactions observed during the breakdown process are discussed in detail in this paper. A detailed description of the flow structures that arise due to these nonlinear interactions is provided and an analysis of the skin friction and heat transfer development during the breakdown is presented. The controlled transition simulations clearly demonstrate that fundamental breakdown may indeed be a viable path to complete breakdown to turbulence in hypersonic cone boundary layers at Mach 6. |
| doi_str_mv | 10.1017/jfm.2014.678 |
| format | Article |
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The motivation for this research is to make a contribution towards understanding the nonlinear stages of transition and the final breakdown to turbulence in hypersonic boundary layers. In particular, the role of second-mode fundamental resonance, or (K-type) breakdown, is investigated using high-resolution ‘controlled’ transition simulations. The simulations were carried out for the laboratory conditions of the hypersonic transition experiments conducted at Purdue University. First, several low-resolution simulations were carried out to explore the parameter space for fundamental resonance in order to identify the cases that result in strong nonlinear interactions. Subsequently, based on the results from this study, a set of highly resolved simulations that proceed deep into the turbulent breakdown region have been performed. The nonlinear interactions observed during the breakdown process are discussed in detail in this paper. A detailed description of the flow structures that arise due to these nonlinear interactions is provided and an analysis of the skin friction and heat transfer development during the breakdown is presented. The controlled transition simulations clearly demonstrate that fundamental breakdown may indeed be a viable path to complete breakdown to turbulence in hypersonic cone boundary layers at Mach 6.</description><identifier>ISSN: 0022-1120</identifier><identifier>EISSN: 1469-7645</identifier><identifier>DOI: 10.1017/jfm.2014.678</identifier><language>eng</language><publisher>Cambridge, UK: Cambridge University Press</publisher><subject>Aerodynamics ; Boundary layer transition ; Boundary layers ; Breakdown ; Computational fluid dynamics ; Design ; Direct numerical simulation ; Experiments ; Flight vehicles ; Fluid flow ; Hypersonic boundary layer ; Hypersonic vehicles ; Laminar boundary layer ; Laminar flow ; Loads (forces) ; Mathematical models ; Physics ; Predictions ; Reynolds number ; Surface temperature ; Thermal analysis ; Thermal protection ; Turbulence ; Turbulent boundary layer ; Turbulent flow ; Vehicles</subject><ispartof>Journal of fluid mechanics, 2015-04, Vol.768, p.175-218</ispartof><rights>2015 Cambridge University Press</rights><lds50>peer_reviewed</lds50><woscitedreferencessubscribed>false</woscitedreferencessubscribed><citedby>FETCH-LOGICAL-c368t-a01197c96b74028f6bbe41e9f9709f1eb31f3e3e32ebfe36559c53c6de3d91e03</citedby><cites>FETCH-LOGICAL-c368t-a01197c96b74028f6bbe41e9f9709f1eb31f3e3e32ebfe36559c53c6de3d91e03</cites></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><linktohtml>$$Uhttps://www.cambridge.org/core/product/identifier/S0022112014006788/type/journal_article$$EHTML$$P50$$Gcambridge$$H</linktohtml><link.rule.ids>164,314,780,784,27924,27925,55628</link.rule.ids></links><search><creatorcontrib>Sivasubramanian, Jayahar</creatorcontrib><creatorcontrib>Fasel, Hermann F.</creatorcontrib><title>Direct numerical simulation of transition in a sharp cone boundary layer at Mach 6: fundamental breakdown</title><title>Journal of fluid mechanics</title><addtitle>J. Fluid Mech</addtitle><description>Direct numerical simulations (DNS) were performed to investigate the laminar–turbulent transition in a boundary layer on a sharp cone with an isothermal wall at Mach 6 and at zero angle of attack. The motivation for this research is to make a contribution towards understanding the nonlinear stages of transition and the final breakdown to turbulence in hypersonic boundary layers. In particular, the role of second-mode fundamental resonance, or (K-type) breakdown, is investigated using high-resolution ‘controlled’ transition simulations. The simulations were carried out for the laboratory conditions of the hypersonic transition experiments conducted at Purdue University. First, several low-resolution simulations were carried out to explore the parameter space for fundamental resonance in order to identify the cases that result in strong nonlinear interactions. Subsequently, based on the results from this study, a set of highly resolved simulations that proceed deep into the turbulent breakdown region have been performed. The nonlinear interactions observed during the breakdown process are discussed in detail in this paper. A detailed description of the flow structures that arise due to these nonlinear interactions is provided and an analysis of the skin friction and heat transfer development during the breakdown is presented. The controlled transition simulations clearly demonstrate that fundamental breakdown may indeed be a viable path to complete breakdown to turbulence in hypersonic cone boundary layers at Mach 6.</description><subject>Aerodynamics</subject><subject>Boundary layer transition</subject><subject>Boundary layers</subject><subject>Breakdown</subject><subject>Computational fluid dynamics</subject><subject>Design</subject><subject>Direct numerical simulation</subject><subject>Experiments</subject><subject>Flight vehicles</subject><subject>Fluid flow</subject><subject>Hypersonic boundary layer</subject><subject>Hypersonic vehicles</subject><subject>Laminar boundary layer</subject><subject>Laminar flow</subject><subject>Loads (forces)</subject><subject>Mathematical models</subject><subject>Physics</subject><subject>Predictions</subject><subject>Reynolds number</subject><subject>Surface temperature</subject><subject>Thermal analysis</subject><subject>Thermal protection</subject><subject>Turbulence</subject><subject>Turbulent boundary layer</subject><subject>Turbulent flow</subject><subject>Vehicles</subject><issn>0022-1120</issn><issn>1469-7645</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2015</creationdate><recordtype>article</recordtype><sourceid>8G5</sourceid><sourceid>ABUWG</sourceid><sourceid>AFKRA</sourceid><sourceid>AZQEC</sourceid><sourceid>BENPR</sourceid><sourceid>CCPQU</sourceid><sourceid>DWQXO</sourceid><sourceid>GNUQQ</sourceid><sourceid>GUQSH</sourceid><sourceid>M2O</sourceid><recordid>eNptkE1LAzEQhoMoWKs3f0DAq7vmYzfbeBO_oeJFzyHJTmxqN6nJLtJ_79YWvEgOQ5hn3mEehM4pKSmhzdXSdSUjtCpFMztAE1oJWTSiqg_RhBDGCkoZOUYnOS8JoZzIZoL8nU9gexyGDpK3eoWz74aV7n0MODrcJx2y__35gDXOC53W2MYA2MQhtDpt8EpvIGHd4xdtF1hcY7dtdBD6Mc4k0J9t_A6n6MjpVYazfZ2i94f7t9unYv76-Hx7My8sF7O-0IRS2VgpTFMRNnPCGKgoSCcbIh0Fw6njMD4GxgEXdS1tza1ogbeSAuFTdLHLXaf4NUDu1TIOKYwrFatkRQXjTT1SlzvKpphzAqfWyXfjNYoStZWpRplqK1ONMke83OO6M8m3H_CX-u_ADzlHd5s</recordid><startdate>20150410</startdate><enddate>20150410</enddate><creator>Sivasubramanian, Jayahar</creator><creator>Fasel, Hermann F.</creator><general>Cambridge University Press</general><scope>AAYXX</scope><scope>CITATION</scope><scope>3V.</scope><scope>7TB</scope><scope>7U5</scope><scope>7UA</scope><scope>7XB</scope><scope>88I</scope><scope>8FD</scope><scope>8FE</scope><scope>8FG</scope><scope>8FK</scope><scope>8G5</scope><scope>ABJCF</scope><scope>ABUWG</scope><scope>AFKRA</scope><scope>ARAPS</scope><scope>AZQEC</scope><scope>BENPR</scope><scope>BGLVJ</scope><scope>BHPHI</scope><scope>BKSAR</scope><scope>C1K</scope><scope>CCPQU</scope><scope>DWQXO</scope><scope>F1W</scope><scope>FR3</scope><scope>GNUQQ</scope><scope>GUQSH</scope><scope>H8D</scope><scope>H96</scope><scope>HCIFZ</scope><scope>KR7</scope><scope>L.G</scope><scope>L6V</scope><scope>L7M</scope><scope>M2O</scope><scope>M2P</scope><scope>M7S</scope><scope>MBDVC</scope><scope>P5Z</scope><scope>P62</scope><scope>PCBAR</scope><scope>PQEST</scope><scope>PQQKQ</scope><scope>PQUKI</scope><scope>PTHSS</scope><scope>Q9U</scope><scope>S0W</scope></search><sort><creationdate>20150410</creationdate><title>Direct numerical simulation of transition in a sharp cone boundary layer at Mach 6: fundamental breakdown</title><author>Sivasubramanian, Jayahar ; 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Fluid Mech</addtitle><date>2015-04-10</date><risdate>2015</risdate><volume>768</volume><spage>175</spage><epage>218</epage><pages>175-218</pages><issn>0022-1120</issn><eissn>1469-7645</eissn><abstract>Direct numerical simulations (DNS) were performed to investigate the laminar–turbulent transition in a boundary layer on a sharp cone with an isothermal wall at Mach 6 and at zero angle of attack. The motivation for this research is to make a contribution towards understanding the nonlinear stages of transition and the final breakdown to turbulence in hypersonic boundary layers. In particular, the role of second-mode fundamental resonance, or (K-type) breakdown, is investigated using high-resolution ‘controlled’ transition simulations. The simulations were carried out for the laboratory conditions of the hypersonic transition experiments conducted at Purdue University. First, several low-resolution simulations were carried out to explore the parameter space for fundamental resonance in order to identify the cases that result in strong nonlinear interactions. Subsequently, based on the results from this study, a set of highly resolved simulations that proceed deep into the turbulent breakdown region have been performed. The nonlinear interactions observed during the breakdown process are discussed in detail in this paper. A detailed description of the flow structures that arise due to these nonlinear interactions is provided and an analysis of the skin friction and heat transfer development during the breakdown is presented. The controlled transition simulations clearly demonstrate that fundamental breakdown may indeed be a viable path to complete breakdown to turbulence in hypersonic cone boundary layers at Mach 6.</abstract><cop>Cambridge, UK</cop><pub>Cambridge University Press</pub><doi>10.1017/jfm.2014.678</doi><tpages>44</tpages></addata></record> |
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| subjects | Aerodynamics Boundary layer transition Boundary layers Breakdown Computational fluid dynamics Design Direct numerical simulation Experiments Flight vehicles Fluid flow Hypersonic boundary layer Hypersonic vehicles Laminar boundary layer Laminar flow Loads (forces) Mathematical models Physics Predictions Reynolds number Surface temperature Thermal analysis Thermal protection Turbulence Turbulent boundary layer Turbulent flow Vehicles |
| title | Direct numerical simulation of transition in a sharp cone boundary layer at Mach 6: fundamental breakdown |
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