Transition within a Hypervelocity Boundary Layer on a 5-degree Half-Angle Cone in Freestream Air/CO2 Mixtures
The most significant instability mechanism which leads to laminar to turbulent transition in hypervelocity flow over cold, slender bodies, characteristic of high enthalpy facilities like the T5 hypervelocity shock tunnel at Caltech, is the so-called second or Mack mode, which depends upon the amplic...
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| creator | Jewell, Joseph S Wagnild, Ross M Leyva, Ivett A Candler, Graham V Shepherd, Joseph E |
| description | The most significant instability mechanism which leads to laminar to turbulent transition in hypervelocity flow over cold, slender bodies, characteristic of high enthalpy facilities like the T5 hypervelocity shock tunnel at Caltech, is the so-called second or Mack mode, which depends upon the amplication of acoustic disturbances trapped in the boundary layer, as described by Mack (1984). At high Mach number (4) and for cold walls, the first (viscous) mode is damped and higher inviscid modes are amplified, so that the second mode would be expected to be the only mechanism of linear instability leading to transition for a slender cone at zero angle of attack.
The original document contains color images. Presented at the American Institute of Aeronautics and Astronautics (AIAA) Aerospace Sciences Meeting held in Dallas, TX on 7-10 January 2013. |
| format | Report |
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The original document contains color images. Presented at the American Institute of Aeronautics and Astronautics (AIAA) Aerospace Sciences Meeting held in Dallas, TX on 7-10 January 2013.</description><language>eng</language><subject>ANGLE OF ATTACK ; BOUNDARY LAYER ; ENTHALPY ; Fluid Mechanics ; FREE STREAM ; INVISCID FLOW ; LOW TEMPERATURE ; MACH NUMBER ; REYNOLDS NUMBER ; SHOCK TUNNELS ; SLENDER BODIES ; TRAPPING(CHARGED PARTICLES) ; VISCOSITY</subject><creationdate>2013</creationdate><rights>Approved for public release; distribution is unlimited.</rights><oa>free_for_read</oa><woscitedreferencessubscribed>false</woscitedreferencessubscribed></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><link.rule.ids>230,776,881,27546,27547</link.rule.ids><linktorsrc>$$Uhttps://apps.dtic.mil/sti/citations/ADA587774$$EView_record_in_DTIC$$FView_record_in_$$GDTIC$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>Jewell, Joseph S</creatorcontrib><creatorcontrib>Wagnild, Ross M</creatorcontrib><creatorcontrib>Leyva, Ivett A</creatorcontrib><creatorcontrib>Candler, Graham V</creatorcontrib><creatorcontrib>Shepherd, Joseph E</creatorcontrib><creatorcontrib>AIR FORCE RESEARCH LAB EDWARDS AFB CA AEROSPACE SYSTEMS DIRECTORATE</creatorcontrib><title>Transition within a Hypervelocity Boundary Layer on a 5-degree Half-Angle Cone in Freestream Air/CO2 Mixtures</title><description>The most significant instability mechanism which leads to laminar to turbulent transition in hypervelocity flow over cold, slender bodies, characteristic of high enthalpy facilities like the T5 hypervelocity shock tunnel at Caltech, is the so-called second or Mack mode, which depends upon the amplication of acoustic disturbances trapped in the boundary layer, as described by Mack (1984). At high Mach number (4) and for cold walls, the first (viscous) mode is damped and higher inviscid modes are amplified, so that the second mode would be expected to be the only mechanism of linear instability leading to transition for a slender cone at zero angle of attack.
The original document contains color images. Presented at the American Institute of Aeronautics and Astronautics (AIAA) Aerospace Sciences Meeting held in Dallas, TX on 7-10 January 2013.</description><subject>ANGLE OF ATTACK</subject><subject>BOUNDARY LAYER</subject><subject>ENTHALPY</subject><subject>Fluid Mechanics</subject><subject>FREE STREAM</subject><subject>INVISCID FLOW</subject><subject>LOW TEMPERATURE</subject><subject>MACH NUMBER</subject><subject>REYNOLDS NUMBER</subject><subject>SHOCK TUNNELS</subject><subject>SLENDER BODIES</subject><subject>TRAPPING(CHARGED PARTICLES)</subject><subject>VISCOSITY</subject><fulltext>true</fulltext><rsrctype>report</rsrctype><creationdate>2013</creationdate><recordtype>report</recordtype><sourceid>1RU</sourceid><recordid>eNqFizEKwkAQRdNYiHoDi7nAIqghtms0pFBs0oclmcSBza7MTtS9vRHsrT689_48GSo2LpCQd_AiuZMDA2V8ID_R-oYkwtGPrjUc4WIiMvhvkaoWe0aE0thOaddbhNw7hOlfTDwIoxlAE2_y2xau9JaRMSyTWWdswNVvF8m6OFd5qVqhpg5CDqXWJ50esizb7_7oDyPfPag</recordid><startdate>201301</startdate><enddate>201301</enddate><creator>Jewell, Joseph S</creator><creator>Wagnild, Ross M</creator><creator>Leyva, Ivett A</creator><creator>Candler, Graham V</creator><creator>Shepherd, Joseph E</creator><scope>1RU</scope><scope>BHM</scope></search><sort><creationdate>201301</creationdate><title>Transition within a Hypervelocity Boundary Layer on a 5-degree Half-Angle Cone in Freestream Air/CO2 Mixtures</title><author>Jewell, Joseph S ; Wagnild, Ross M ; Leyva, Ivett A ; Candler, Graham V ; Shepherd, Joseph E</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-dtic_stinet_ADA5877743</frbrgroupid><rsrctype>reports</rsrctype><prefilter>reports</prefilter><language>eng</language><creationdate>2013</creationdate><topic>ANGLE OF ATTACK</topic><topic>BOUNDARY LAYER</topic><topic>ENTHALPY</topic><topic>Fluid Mechanics</topic><topic>FREE STREAM</topic><topic>INVISCID FLOW</topic><topic>LOW TEMPERATURE</topic><topic>MACH NUMBER</topic><topic>REYNOLDS NUMBER</topic><topic>SHOCK TUNNELS</topic><topic>SLENDER BODIES</topic><topic>TRAPPING(CHARGED PARTICLES)</topic><topic>VISCOSITY</topic><toplevel>online_resources</toplevel><creatorcontrib>Jewell, Joseph S</creatorcontrib><creatorcontrib>Wagnild, Ross M</creatorcontrib><creatorcontrib>Leyva, Ivett A</creatorcontrib><creatorcontrib>Candler, Graham V</creatorcontrib><creatorcontrib>Shepherd, Joseph E</creatorcontrib><creatorcontrib>AIR FORCE RESEARCH LAB EDWARDS AFB CA AEROSPACE SYSTEMS DIRECTORATE</creatorcontrib><collection>DTIC Technical Reports</collection><collection>DTIC STINET</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>Jewell, Joseph S</au><au>Wagnild, Ross M</au><au>Leyva, Ivett A</au><au>Candler, Graham V</au><au>Shepherd, Joseph E</au><aucorp>AIR FORCE RESEARCH LAB EDWARDS AFB CA AEROSPACE SYSTEMS DIRECTORATE</aucorp><format>book</format><genre>unknown</genre><ristype>RPRT</ristype><btitle>Transition within a Hypervelocity Boundary Layer on a 5-degree Half-Angle Cone in Freestream Air/CO2 Mixtures</btitle><date>2013-01</date><risdate>2013</risdate><abstract>The most significant instability mechanism which leads to laminar to turbulent transition in hypervelocity flow over cold, slender bodies, characteristic of high enthalpy facilities like the T5 hypervelocity shock tunnel at Caltech, is the so-called second or Mack mode, which depends upon the amplication of acoustic disturbances trapped in the boundary layer, as described by Mack (1984). At high Mach number (4) and for cold walls, the first (viscous) mode is damped and higher inviscid modes are amplified, so that the second mode would be expected to be the only mechanism of linear instability leading to transition for a slender cone at zero angle of attack.
The original document contains color images. Presented at the American Institute of Aeronautics and Astronautics (AIAA) Aerospace Sciences Meeting held in Dallas, TX on 7-10 January 2013.</abstract><oa>free_for_read</oa></addata></record> |
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| subjects | ANGLE OF ATTACK BOUNDARY LAYER ENTHALPY Fluid Mechanics FREE STREAM INVISCID FLOW LOW TEMPERATURE MACH NUMBER REYNOLDS NUMBER SHOCK TUNNELS SLENDER BODIES TRAPPING(CHARGED PARTICLES) VISCOSITY |
| title | Transition within a Hypervelocity Boundary Layer on a 5-degree Half-Angle Cone in Freestream Air/CO2 Mixtures |
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