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Control of stationary cross-flow modes in a Mach 6 boundary layer using patterned roughness
Experiments were performed to investigate passive discrete roughness for transition control on a sharp right-circular cone at an angle of attack at Mach 6.0. A cone angle of attack of $6^{\circ }$ was set to produce a mean cross-flow velocity component in the boundary layer over the cone by which th...
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Published in: | Journal of fluid mechanics 2018-12, Vol.856, p.822-849 |
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description | Experiments were performed to investigate passive discrete roughness for transition control on a sharp right-circular cone at an angle of attack at Mach 6.0. A cone angle of attack of
$6^{\circ }$
was set to produce a mean cross-flow velocity component in the boundary layer over the cone by which the cross-flow instability was the dominant mechanism of turbulent transition. The approach to transition control is based on exciting less-amplified (subcritical) stationary cross-flow modes through the addition of discrete roughness that suppresses the growth of the more-amplified (critical) cross-flow modes, and thereby delays transition. The passive roughness consisted of indentations (dimples) that were evenly spaced around the cone at an axial location that was just upstream of the first linear stability neutral growth branch for cross-flow modes. The experiments were performed in the air force academy (AFA) Mach 6.0 Ludwieg Tube Facility. The cone model was equipped with a motorized three-dimensional traversing mechanism that mounted on the support sting. The traversing mechanism held a closely spaced pair of fast-response total pressure Pitot probes. The measurements consisted of surface oil flow visualization and off-wall azimuthal profiles of mean and fluctuating total pressure at different axial locations. These documented an 25 % increase in the transition Reynolds number with the subcritical roughness. In addition, the experiments revealed evidence of a nonlinear, sum and difference interaction between stationary and travelling cross-flow modes that might indicate a mechanism of early transition in conventional (noisy) hypersonic wind tunnels. |
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$6^{\circ }$
was set to produce a mean cross-flow velocity component in the boundary layer over the cone by which the cross-flow instability was the dominant mechanism of turbulent transition. The approach to transition control is based on exciting less-amplified (subcritical) stationary cross-flow modes through the addition of discrete roughness that suppresses the growth of the more-amplified (critical) cross-flow modes, and thereby delays transition. The passive roughness consisted of indentations (dimples) that were evenly spaced around the cone at an axial location that was just upstream of the first linear stability neutral growth branch for cross-flow modes. The experiments were performed in the air force academy (AFA) Mach 6.0 Ludwieg Tube Facility. The cone model was equipped with a motorized three-dimensional traversing mechanism that mounted on the support sting. The traversing mechanism held a closely spaced pair of fast-response total pressure Pitot probes. The measurements consisted of surface oil flow visualization and off-wall azimuthal profiles of mean and fluctuating total pressure at different axial locations. These documented an 25 % increase in the transition Reynolds number with the subcritical roughness. In addition, the experiments revealed evidence of a nonlinear, sum and difference interaction between stationary and travelling cross-flow modes that might indicate a mechanism of early transition in conventional (noisy) hypersonic wind tunnels.</description><identifier>ISSN: 0022-1120</identifier><identifier>EISSN: 1469-7645</identifier><identifier>DOI: 10.1017/jfm.2018.636</identifier><language>eng</language><publisher>Cambridge, UK: Cambridge University Press</publisher><subject>Aerodynamics ; Amplification ; Angle of attack ; Boundary layer stability ; Boundary layers ; Circular cones ; Computational fluid dynamics ; Control ; Cross flow ; Dimpling ; Experiments ; Flow stability ; Flow velocity ; Flow visualization ; Fluid flow ; Fluid mechanics ; Hypersonic wind tunnels ; Instability ; JFM Papers ; Modes ; Pressure ; Profiles ; Reynolds number ; Roughness ; Three dimensional models ; Vortices ; Wind tunnels</subject><ispartof>Journal of fluid mechanics, 2018-12, Vol.856, p.822-849</ispartof><rights>2018 Cambridge University Press</rights><lds50>peer_reviewed</lds50><woscitedreferencessubscribed>false</woscitedreferencessubscribed><citedby>FETCH-LOGICAL-c302t-b87ac237149bf4dca0428f88717892390be760d7fab0b078c94f581a0c2eb9893</citedby><cites>FETCH-LOGICAL-c302t-b87ac237149bf4dca0428f88717892390be760d7fab0b078c94f581a0c2eb9893</cites><orcidid>0000-0001-8980-1100</orcidid></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><linktohtml>$$Uhttps://www.cambridge.org/core/product/identifier/S0022112018006365/type/journal_article$$EHTML$$P50$$Gcambridge$$H</linktohtml><link.rule.ids>314,780,784,27924,27925,72960</link.rule.ids></links><search><creatorcontrib>Corke, Thomas</creatorcontrib><creatorcontrib>Arndt, Alexander</creatorcontrib><creatorcontrib>Matlis, Eric</creatorcontrib><creatorcontrib>Semper, Michael</creatorcontrib><title>Control of stationary cross-flow modes in a Mach 6 boundary layer using patterned roughness</title><title>Journal of fluid mechanics</title><addtitle>J. Fluid Mech</addtitle><description>Experiments were performed to investigate passive discrete roughness for transition control on a sharp right-circular cone at an angle of attack at Mach 6.0. A cone angle of attack of
$6^{\circ }$
was set to produce a mean cross-flow velocity component in the boundary layer over the cone by which the cross-flow instability was the dominant mechanism of turbulent transition. The approach to transition control is based on exciting less-amplified (subcritical) stationary cross-flow modes through the addition of discrete roughness that suppresses the growth of the more-amplified (critical) cross-flow modes, and thereby delays transition. The passive roughness consisted of indentations (dimples) that were evenly spaced around the cone at an axial location that was just upstream of the first linear stability neutral growth branch for cross-flow modes. The experiments were performed in the air force academy (AFA) Mach 6.0 Ludwieg Tube Facility. The cone model was equipped with a motorized three-dimensional traversing mechanism that mounted on the support sting. The traversing mechanism held a closely spaced pair of fast-response total pressure Pitot probes. The measurements consisted of surface oil flow visualization and off-wall azimuthal profiles of mean and fluctuating total pressure at different axial locations. These documented an 25 % increase in the transition Reynolds number with the subcritical roughness. In addition, the experiments revealed evidence of a nonlinear, sum and difference interaction between stationary and travelling cross-flow modes that might indicate a mechanism of early transition in conventional (noisy) hypersonic wind tunnels.</description><subject>Aerodynamics</subject><subject>Amplification</subject><subject>Angle of attack</subject><subject>Boundary layer stability</subject><subject>Boundary layers</subject><subject>Circular cones</subject><subject>Computational fluid dynamics</subject><subject>Control</subject><subject>Cross flow</subject><subject>Dimpling</subject><subject>Experiments</subject><subject>Flow stability</subject><subject>Flow velocity</subject><subject>Flow visualization</subject><subject>Fluid flow</subject><subject>Fluid mechanics</subject><subject>Hypersonic wind tunnels</subject><subject>Instability</subject><subject>JFM Papers</subject><subject>Modes</subject><subject>Pressure</subject><subject>Profiles</subject><subject>Reynolds number</subject><subject>Roughness</subject><subject>Three dimensional models</subject><subject>Vortices</subject><subject>Wind tunnels</subject><issn>0022-1120</issn><issn>1469-7645</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2018</creationdate><recordtype>article</recordtype><recordid>eNptkD1PwzAURS0EEqWw8QMssZLwbCexPaKKL6mIBSYGy07sNlViFzsR6r8npZVYmN5y3r26B6FrAjkBwu82rs8pEJFXrDpBM1JUMuNVUZ6iGQClGSEUztFFShsAwkDyGfpcBD_E0OHgcBr00Aav4w7XMaSUuS584z40NuHWY41fdb3GFTZh9M2e6vTORjym1q_wVg-Djd42OIZxtfY2pUt05nSX7NXxztHH48P74jlbvj29LO6XWc2ADpkRXNeUcVJI44qm1lBQ4YTghAtJmQRjeQUNd9qAAS5qWbhSEA01tUYKyebo5pC7jeFrtGlQmzBGP1UqSknFGZNlOVG3B-p3W7RObWPbTzMUAbXXpyZ9aq9PTfomPD_iujexbVb2L_Xfhx-J2XIL</recordid><startdate>20181210</startdate><enddate>20181210</enddate><creator>Corke, Thomas</creator><creator>Arndt, Alexander</creator><creator>Matlis, Eric</creator><creator>Semper, Michael</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><orcidid>https://orcid.org/0000-0001-8980-1100</orcidid></search><sort><creationdate>20181210</creationdate><title>Control of stationary cross-flow modes in a Mach 6 boundary layer using patterned roughness</title><author>Corke, Thomas ; Arndt, Alexander ; Matlis, Eric ; Semper, Michael</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-c302t-b87ac237149bf4dca0428f88717892390be760d7fab0b078c94f581a0c2eb9893</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2018</creationdate><topic>Aerodynamics</topic><topic>Amplification</topic><topic>Angle of attack</topic><topic>Boundary layer stability</topic><topic>Boundary layers</topic><topic>Circular cones</topic><topic>Computational fluid dynamics</topic><topic>Control</topic><topic>Cross flow</topic><topic>Dimpling</topic><topic>Experiments</topic><topic>Flow stability</topic><topic>Flow velocity</topic><topic>Flow visualization</topic><topic>Fluid flow</topic><topic>Fluid mechanics</topic><topic>Hypersonic wind tunnels</topic><topic>Instability</topic><topic>JFM Papers</topic><topic>Modes</topic><topic>Pressure</topic><topic>Profiles</topic><topic>Reynolds number</topic><topic>Roughness</topic><topic>Three dimensional models</topic><topic>Vortices</topic><topic>Wind tunnels</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Corke, Thomas</creatorcontrib><creatorcontrib>Arndt, Alexander</creatorcontrib><creatorcontrib>Matlis, Eric</creatorcontrib><creatorcontrib>Semper, Michael</creatorcontrib><collection>CrossRef</collection><collection>ProQuest Central (Corporate)</collection><collection>Mechanical & Transportation Engineering Abstracts</collection><collection>Solid State and Superconductivity Abstracts</collection><collection>Water Resources Abstracts</collection><collection>ProQuest Central (purchase pre-March 2016)</collection><collection>Science Database (Alumni Edition)</collection><collection>Technology Research Database</collection><collection>ProQuest SciTech Collection</collection><collection>ProQuest Technology Collection</collection><collection>ProQuest Central (Alumni) (purchase pre-March 2016)</collection><collection>Research Library (Alumni Edition)</collection><collection>Materials Science & Engineering Collection</collection><collection>ProQuest Central (Alumni)</collection><collection>ProQuest Central</collection><collection>Advanced Technologies & Aerospace Database (1962 - current)</collection><collection>ProQuest Central Essentials</collection><collection>AUTh Library subscriptions: ProQuest Central</collection><collection>Technology Collection</collection><collection>ProQuest Natural Science Collection</collection><collection>Earth, Atmospheric & Aquatic Science Collection</collection><collection>Environmental Sciences and Pollution Management</collection><collection>ProQuest One Community College</collection><collection>ProQuest Central Korea</collection><collection>ASFA: Aquatic Sciences and Fisheries Abstracts</collection><collection>Engineering Research Database</collection><collection>ProQuest Central Student</collection><collection>Research Library Prep</collection><collection>Aerospace Database</collection><collection>Aquatic Science & Fisheries Abstracts (ASFA) 2: Ocean Technology, Policy & Non-Living Resources</collection><collection>SciTech Premium Collection (Proquest) (PQ_SDU_P3)</collection><collection>Civil Engineering Abstracts</collection><collection>Aquatic Science & Fisheries Abstracts (ASFA) Professional</collection><collection>ProQuest Engineering Collection</collection><collection>Advanced Technologies Database with Aerospace</collection><collection>ProQuest research library</collection><collection>ProQuest Science Journals</collection><collection>Engineering Database</collection><collection>Research Library (Corporate)</collection><collection>ProQuest advanced technologies & aerospace journals</collection><collection>ProQuest Advanced Technologies & Aerospace Collection</collection><collection>Earth, Atmospheric & Aquatic Science Database</collection><collection>ProQuest One Academic Eastern Edition (DO NOT USE)</collection><collection>ProQuest One Academic</collection><collection>ProQuest One Academic UKI Edition</collection><collection>Engineering collection</collection><collection>ProQuest Central Basic</collection><collection>DELNET Engineering & Technology Collection</collection><jtitle>Journal of fluid mechanics</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>Corke, Thomas</au><au>Arndt, Alexander</au><au>Matlis, Eric</au><au>Semper, Michael</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Control of stationary cross-flow modes in a Mach 6 boundary layer using patterned roughness</atitle><jtitle>Journal of fluid mechanics</jtitle><addtitle>J. Fluid Mech</addtitle><date>2018-12-10</date><risdate>2018</risdate><volume>856</volume><spage>822</spage><epage>849</epage><pages>822-849</pages><issn>0022-1120</issn><eissn>1469-7645</eissn><abstract>Experiments were performed to investigate passive discrete roughness for transition control on a sharp right-circular cone at an angle of attack at Mach 6.0. A cone angle of attack of
$6^{\circ }$
was set to produce a mean cross-flow velocity component in the boundary layer over the cone by which the cross-flow instability was the dominant mechanism of turbulent transition. The approach to transition control is based on exciting less-amplified (subcritical) stationary cross-flow modes through the addition of discrete roughness that suppresses the growth of the more-amplified (critical) cross-flow modes, and thereby delays transition. The passive roughness consisted of indentations (dimples) that were evenly spaced around the cone at an axial location that was just upstream of the first linear stability neutral growth branch for cross-flow modes. The experiments were performed in the air force academy (AFA) Mach 6.0 Ludwieg Tube Facility. The cone model was equipped with a motorized three-dimensional traversing mechanism that mounted on the support sting. The traversing mechanism held a closely spaced pair of fast-response total pressure Pitot probes. The measurements consisted of surface oil flow visualization and off-wall azimuthal profiles of mean and fluctuating total pressure at different axial locations. These documented an 25 % increase in the transition Reynolds number with the subcritical roughness. In addition, the experiments revealed evidence of a nonlinear, sum and difference interaction between stationary and travelling cross-flow modes that might indicate a mechanism of early transition in conventional (noisy) hypersonic wind tunnels.</abstract><cop>Cambridge, UK</cop><pub>Cambridge University Press</pub><doi>10.1017/jfm.2018.636</doi><tpages>28</tpages><orcidid>https://orcid.org/0000-0001-8980-1100</orcidid></addata></record> |
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subjects | Aerodynamics Amplification Angle of attack Boundary layer stability Boundary layers Circular cones Computational fluid dynamics Control Cross flow Dimpling Experiments Flow stability Flow velocity Flow visualization Fluid flow Fluid mechanics Hypersonic wind tunnels Instability JFM Papers Modes Pressure Profiles Reynolds number Roughness Three dimensional models Vortices Wind tunnels |
title | Control of stationary cross-flow modes in a Mach 6 boundary layer using patterned roughness |
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