Laminar Near Wake of a Circular Cylinder at Hypersonic Speeds
The laminar near-wake flow behind a circular cylinder at hypersonic speeds has been examined experimentally and analytically. Surface pressure and heat flux measurements were obtained in a free-piston shock tunnel at a nominal Mach number of 10. The freestream unit Reynolds numbers were 3:02 x 10......
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| Veröffentlicht in: | AIAA journal 2010-01, Vol.48 (1), p.236-248 |
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| creator | Park, Gisu Gai, Sudhir L Neely, Andrew J |
| description | The laminar near-wake flow behind a circular cylinder at hypersonic speeds has been examined experimentally and analytically. Surface pressure and heat flux measurements were obtained in a free-piston shock tunnel at a nominal Mach number of 10. The freestream unit Reynolds numbers were 3:02 x 10.../m and 11:7 x 10.../m at total specific enthalpies of 13.35 and 3:94 MJ=kg, respectively. The experimental data of surface pressure and heat flux showed good agreement with theory based on perfect gas. Unlike surface pressure, the surface heat flux depended strongly on the wall-to-total-temperature ratio, and it increased with increase in the ratio. The surface pressure, however, depended on the Reynolds number, although this dependency was found to be weak. The flow separation angles behind the cylinder showed an inverse of the square root of Reynolds number dependence similar to the low-speed laminar flow separation behind a circular cylinder. (ProQuest: ... denotes formulae/symbols omitted.) |
| doi_str_mv | 10.2514/1.44167 |
| format | Article |
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Surface pressure and heat flux measurements were obtained in a free-piston shock tunnel at a nominal Mach number of 10. The freestream unit Reynolds numbers were 3:02 x 10.../m and 11:7 x 10.../m at total specific enthalpies of 13.35 and 3:94 MJ=kg, respectively. The experimental data of surface pressure and heat flux showed good agreement with theory based on perfect gas. Unlike surface pressure, the surface heat flux depended strongly on the wall-to-total-temperature ratio, and it increased with increase in the ratio. The surface pressure, however, depended on the Reynolds number, although this dependency was found to be weak. The flow separation angles behind the cylinder showed an inverse of the square root of Reynolds number dependence similar to the low-speed laminar flow separation behind a circular cylinder. (ProQuest: ... denotes formulae/symbols omitted.)</description><identifier>ISSN: 0001-1452</identifier><identifier>EISSN: 1533-385X</identifier><identifier>DOI: 10.2514/1.44167</identifier><identifier>CODEN: AIAJAH</identifier><language>eng</language><publisher>Reston, VA: American Institute of Aeronautics and Astronautics</publisher><subject>Aerodynamics ; Aircraft ; Compressible flows; shock and detonation phenomena ; Exact sciences and technology ; Fluid dynamics ; Fundamental areas of phenomenology (including applications) ; Noise ; Physics ; Reynolds number ; Supersonic and hypersonic flows ; Turbulent flow ; Turbulent flows, convection, and heat transfer ; Velocity ; Wakes</subject><ispartof>AIAA journal, 2010-01, Vol.48 (1), p.236-248</ispartof><rights>2015 INIST-CNRS</rights><rights>Copyright American Institute of Aeronautics and Astronautics Jan 2010</rights><lds50>peer_reviewed</lds50><woscitedreferencessubscribed>false</woscitedreferencessubscribed><citedby>FETCH-LOGICAL-a442t-d6b232ce94af50607a177bf5bbbc22be188a2db2f3615cae665046123ff15c743</citedby><cites>FETCH-LOGICAL-a442t-d6b232ce94af50607a177bf5bbbc22be188a2db2f3615cae665046123ff15c743</cites></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><link.rule.ids>314,780,784,4024,27923,27924,27925</link.rule.ids><backlink>$$Uhttp://pascal-francis.inist.fr/vibad/index.php?action=getRecordDetail&idt=22333390$$DView record in Pascal Francis$$Hfree_for_read</backlink></links><search><creatorcontrib>Park, Gisu</creatorcontrib><creatorcontrib>Gai, Sudhir L</creatorcontrib><creatorcontrib>Neely, Andrew J</creatorcontrib><title>Laminar Near Wake of a Circular Cylinder at Hypersonic Speeds</title><title>AIAA journal</title><description>The laminar near-wake flow behind a circular cylinder at hypersonic speeds has been examined experimentally and analytically. Surface pressure and heat flux measurements were obtained in a free-piston shock tunnel at a nominal Mach number of 10. The freestream unit Reynolds numbers were 3:02 x 10.../m and 11:7 x 10.../m at total specific enthalpies of 13.35 and 3:94 MJ=kg, respectively. The experimental data of surface pressure and heat flux showed good agreement with theory based on perfect gas. Unlike surface pressure, the surface heat flux depended strongly on the wall-to-total-temperature ratio, and it increased with increase in the ratio. The surface pressure, however, depended on the Reynolds number, although this dependency was found to be weak. The flow separation angles behind the cylinder showed an inverse of the square root of Reynolds number dependence similar to the low-speed laminar flow separation behind a circular cylinder. (ProQuest: ... denotes formulae/symbols omitted.)</description><subject>Aerodynamics</subject><subject>Aircraft</subject><subject>Compressible flows; shock and detonation phenomena</subject><subject>Exact sciences and technology</subject><subject>Fluid dynamics</subject><subject>Fundamental areas of phenomenology (including applications)</subject><subject>Noise</subject><subject>Physics</subject><subject>Reynolds number</subject><subject>Supersonic and hypersonic flows</subject><subject>Turbulent flow</subject><subject>Turbulent flows, convection, and heat transfer</subject><subject>Velocity</subject><subject>Wakes</subject><issn>0001-1452</issn><issn>1533-385X</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2010</creationdate><recordtype>article</recordtype><recordid>eNpt0E1LAzEQBuAgCtYq_oVF_MDD1mTyse3BgxS1QtGDit7CbDaBrdvdNdkF---NtiiIOSRMeHhnGEIOGR2BZOKCjYRgKtsiAyY5T_lYvm6TAaWUpUxI2CV7ISxiBdmYDcjlHJdljT65t_F6wTebNC7BZFp601fxa7qqyrqwPsEuma1a60NTlyZ5bK0twj7ZcVgFe7B5h-T55vppOkvnD7d306t5ikJAlxYqBw7GTgQ6SRXNkGVZ7mSe5wYgt2w8RihycFwxadAqJalQDLhzsc4EH5LTdW7rm_fehk4vy2BsVWFtmz5orvgEQKoIj_7ARdP7Os6mIa4DMplNIjpbI-ObELx1uvXlEv1KM6q_dqiZ_t5hlCebOAwGK-exNmX44QA8ngmN7nztsET8bbmJ0W3htOurqrMfXbTH_9o_rT8BhGOHmw</recordid><startdate>201001</startdate><enddate>201001</enddate><creator>Park, Gisu</creator><creator>Gai, Sudhir L</creator><creator>Neely, Andrew J</creator><general>American Institute of Aeronautics and Astronautics</general><scope>IQODW</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>201001</creationdate><title>Laminar Near Wake of a Circular Cylinder at Hypersonic Speeds</title><author>Park, Gisu ; Gai, Sudhir L ; Neely, Andrew J</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-a442t-d6b232ce94af50607a177bf5bbbc22be188a2db2f3615cae665046123ff15c743</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2010</creationdate><topic>Aerodynamics</topic><topic>Aircraft</topic><topic>Compressible flows; shock and detonation phenomena</topic><topic>Exact sciences and technology</topic><topic>Fluid dynamics</topic><topic>Fundamental areas of phenomenology (including applications)</topic><topic>Noise</topic><topic>Physics</topic><topic>Reynolds number</topic><topic>Supersonic and hypersonic flows</topic><topic>Turbulent flow</topic><topic>Turbulent flows, convection, and heat transfer</topic><topic>Velocity</topic><topic>Wakes</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Park, Gisu</creatorcontrib><creatorcontrib>Gai, Sudhir L</creatorcontrib><creatorcontrib>Neely, Andrew J</creatorcontrib><collection>Pascal-Francis</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>AIAA journal</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>Park, Gisu</au><au>Gai, Sudhir L</au><au>Neely, Andrew J</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Laminar Near Wake of a Circular Cylinder at Hypersonic Speeds</atitle><jtitle>AIAA journal</jtitle><date>2010-01</date><risdate>2010</risdate><volume>48</volume><issue>1</issue><spage>236</spage><epage>248</epage><pages>236-248</pages><issn>0001-1452</issn><eissn>1533-385X</eissn><coden>AIAJAH</coden><abstract>The laminar near-wake flow behind a circular cylinder at hypersonic speeds has been examined experimentally and analytically. Surface pressure and heat flux measurements were obtained in a free-piston shock tunnel at a nominal Mach number of 10. The freestream unit Reynolds numbers were 3:02 x 10.../m and 11:7 x 10.../m at total specific enthalpies of 13.35 and 3:94 MJ=kg, respectively. The experimental data of surface pressure and heat flux showed good agreement with theory based on perfect gas. Unlike surface pressure, the surface heat flux depended strongly on the wall-to-total-temperature ratio, and it increased with increase in the ratio. The surface pressure, however, depended on the Reynolds number, although this dependency was found to be weak. The flow separation angles behind the cylinder showed an inverse of the square root of Reynolds number dependence similar to the low-speed laminar flow separation behind a circular cylinder. (ProQuest: ... denotes formulae/symbols omitted.)</abstract><cop>Reston, VA</cop><pub>American Institute of Aeronautics and Astronautics</pub><doi>10.2514/1.44167</doi><tpages>13</tpages></addata></record> |
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| ispartof | AIAA journal, 2010-01, Vol.48 (1), p.236-248 |
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| language | eng |
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| subjects | Aerodynamics Aircraft Compressible flows shock and detonation phenomena Exact sciences and technology Fluid dynamics Fundamental areas of phenomenology (including applications) Noise Physics Reynolds number Supersonic and hypersonic flows Turbulent flow Turbulent flows, convection, and heat transfer Velocity Wakes |
| title | Laminar Near Wake of a Circular Cylinder at Hypersonic Speeds |
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