Control of Pseudo-Shock by Slot Injection
It is well known that the boundary layer separation due to the adverse pressure gradient of the pseudo-shock affects the dynamic feature of the pseudo-shock such as the shape of the first shock, the pressure recovery and the self-induced oscillation. The suppression of the separation is effective to...
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| Veröffentlicht in: | JSME International Journal Series B Fluids and Thermal Engineering 2002, Vol.45(1), pp.150-157 |
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| container_title | JSME International Journal Series B Fluids and Thermal Engineering |
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| creator | OKUI, Hidetaka HIRAKI, Hisashi PARK, Myeong-Kwan OSHIMA, Shuzo YAMANE, Ryuichiro |
| description | It is well known that the boundary layer separation due to the adverse pressure gradient of the pseudo-shock affects the dynamic feature of the pseudo-shock such as the shape of the first shock, the pressure recovery and the self-induced oscillation. The suppression of the separation is effective to control the interaction between the shock wave and the boundary layer. In this research, the boundary layer control with the slot injection is studied experimentally and numerically. The experiment is carried out in a blow-down supersonic wind tunnel at free stream Mach number of 2.0. The numerical simulation is made with the two-dimensional compressible Navier-Stokes code. In solving the equations, the second-order accurate Harten-Yee's upwind TVD scheme and k-ε turbulence model modified for the compressible flow are used. The results show that the separation is appreciably suppressed and the shape of the first shock is changed, resulting the wall pressure fluctuation to be greatly reduced. Furthermore the total pressure loss is decreased with the low slot height. |
| doi_str_mv | 10.1299/jsmeb.45.150 |
| format | Article |
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The suppression of the separation is effective to control the interaction between the shock wave and the boundary layer. In this research, the boundary layer control with the slot injection is studied experimentally and numerically. The experiment is carried out in a blow-down supersonic wind tunnel at free stream Mach number of 2.0. The numerical simulation is made with the two-dimensional compressible Navier-Stokes code. In solving the equations, the second-order accurate Harten-Yee's upwind TVD scheme and k-ε turbulence model modified for the compressible flow are used. The results show that the separation is appreciably suppressed and the shape of the first shock is changed, resulting the wall pressure fluctuation to be greatly reduced. Furthermore the total pressure loss is decreased with the low slot height.</description><identifier>ISSN: 1340-8054</identifier><identifier>EISSN: 1347-5371</identifier><identifier>DOI: 10.1299/jsmeb.45.150</identifier><language>eng</language><publisher>Tokyo: The Japan Society of Mechanical Engineers</publisher><subject>Boundary Layer ; Boundary Layer Control ; Compressible flows; shock and detonation phenomena ; Exact sciences and technology ; Flow control ; Fluid dynamics ; Fundamental areas of phenomenology (including applications) ; Passive Control ; Physics ; Pseudo-Shock ; Shock Train ; Shock Wave ; Shock-wave interactions and shock effects ; Shock-wave interactions and shockeffects ; Supersonic Flow</subject><ispartof>JSME International Journal Series B Fluids and Thermal Engineering, 2002, Vol.45(1), pp.150-157</ispartof><rights>2002 by The Japan Society of Mechanical Engineers</rights><rights>2002 INIST-CNRS</rights><rights>Copyright Japan Science and Technology Agency 2002</rights><lds50>peer_reviewed</lds50><oa>free_for_read</oa><woscitedreferencessubscribed>false</woscitedreferencessubscribed><citedby>FETCH-LOGICAL-c566t-9c0bedcafcf277d760c3a97132ce3c40d60cad28e399dabff0134624eb1bdf193</citedby><cites>FETCH-LOGICAL-c566t-9c0bedcafcf277d760c3a97132ce3c40d60cad28e399dabff0134624eb1bdf193</cites></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><link.rule.ids>314,780,784,1882,27923,27924</link.rule.ids><backlink>$$Uhttp://pascal-francis.inist.fr/vibad/index.php?action=getRecordDetail&idt=13641807$$DView record in Pascal Francis$$Hfree_for_read</backlink></links><search><creatorcontrib>OKUI, Hidetaka</creatorcontrib><creatorcontrib>HIRAKI, Hisashi</creatorcontrib><creatorcontrib>PARK, Myeong-Kwan</creatorcontrib><creatorcontrib>OSHIMA, Shuzo</creatorcontrib><creatorcontrib>YAMANE, Ryuichiro</creatorcontrib><title>Control of Pseudo-Shock by Slot Injection</title><title>JSME International Journal Series B Fluids and Thermal Engineering</title><description>It is well known that the boundary layer separation due to the adverse pressure gradient of the pseudo-shock affects the dynamic feature of the pseudo-shock such as the shape of the first shock, the pressure recovery and the self-induced oscillation. The suppression of the separation is effective to control the interaction between the shock wave and the boundary layer. In this research, the boundary layer control with the slot injection is studied experimentally and numerically. The experiment is carried out in a blow-down supersonic wind tunnel at free stream Mach number of 2.0. The numerical simulation is made with the two-dimensional compressible Navier-Stokes code. In solving the equations, the second-order accurate Harten-Yee's upwind TVD scheme and k-ε turbulence model modified for the compressible flow are used. The results show that the separation is appreciably suppressed and the shape of the first shock is changed, resulting the wall pressure fluctuation to be greatly reduced. Furthermore the total pressure loss is decreased with the low slot height.</description><subject>Boundary Layer</subject><subject>Boundary Layer Control</subject><subject>Compressible flows; shock and detonation phenomena</subject><subject>Exact sciences and technology</subject><subject>Flow control</subject><subject>Fluid dynamics</subject><subject>Fundamental areas of phenomenology (including applications)</subject><subject>Passive Control</subject><subject>Physics</subject><subject>Pseudo-Shock</subject><subject>Shock Train</subject><subject>Shock Wave</subject><subject>Shock-wave interactions and shock effects</subject><subject>Shock-wave interactions and shockeffects</subject><subject>Supersonic Flow</subject><issn>1340-8054</issn><issn>1347-5371</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2002</creationdate><recordtype>article</recordtype><recordid>eNpdkF1LwzAUhoMoOKd3_oCCKAh2Js1XczmGH4OBwvQ6pGniWrtmJu3F_r1xHVO8OedwznNeXl4ALhGcoEyI-zqsTTEhdIIoPAIjhAlPKeboeDfDNIeUnIKzEGoIMaZMjMDtzLWdd03ibPIaTF-6dLly-jMptsmycV0yb2uju8q15-DEqiaYi30fg_fHh7fZc7p4eZrPpotUU8a6VGhYmFIrq23GeckZ1FgJjnCmDdYElnGhyiw3WIhSFdbCaI1lxBSoKC0SeAxuBt2Nd1-9CZ1cV0GbplGtcX2QGYd5zlgewat_YO1630ZvEhHGaUYogpG6GyjtXQjeWLnx1Vr5rURQ_qQmd6lJQmVMLeLXe1EVtGqsV62uwu8PZgTlkEduOnB16NSHOQDKd5VuzB_RoUTtw02vlJemxd9afYP0</recordid><startdate>20020101</startdate><enddate>20020101</enddate><creator>OKUI, Hidetaka</creator><creator>HIRAKI, Hisashi</creator><creator>PARK, Myeong-Kwan</creator><creator>OSHIMA, Shuzo</creator><creator>YAMANE, Ryuichiro</creator><general>The Japan Society of Mechanical Engineers</general><general>Japan Society of Mechanical Engineers</general><general>Japan Science and Technology Agency</general><scope>IQODW</scope><scope>AAYXX</scope><scope>CITATION</scope><scope>7TB</scope><scope>8FD</scope><scope>FR3</scope><scope>H8D</scope><scope>KR7</scope><scope>L7M</scope></search><sort><creationdate>20020101</creationdate><title>Control of Pseudo-Shock by Slot Injection</title><author>OKUI, Hidetaka ; HIRAKI, Hisashi ; PARK, Myeong-Kwan ; OSHIMA, Shuzo ; YAMANE, Ryuichiro</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-c566t-9c0bedcafcf277d760c3a97132ce3c40d60cad28e399dabff0134624eb1bdf193</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2002</creationdate><topic>Boundary Layer</topic><topic>Boundary Layer Control</topic><topic>Compressible flows; shock and detonation phenomena</topic><topic>Exact sciences and technology</topic><topic>Flow control</topic><topic>Fluid dynamics</topic><topic>Fundamental areas of phenomenology (including applications)</topic><topic>Passive Control</topic><topic>Physics</topic><topic>Pseudo-Shock</topic><topic>Shock Train</topic><topic>Shock Wave</topic><topic>Shock-wave interactions and shock effects</topic><topic>Shock-wave interactions and shockeffects</topic><topic>Supersonic Flow</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>OKUI, Hidetaka</creatorcontrib><creatorcontrib>HIRAKI, Hisashi</creatorcontrib><creatorcontrib>PARK, Myeong-Kwan</creatorcontrib><creatorcontrib>OSHIMA, Shuzo</creatorcontrib><creatorcontrib>YAMANE, Ryuichiro</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>Civil Engineering Abstracts</collection><collection>Advanced Technologies Database with Aerospace</collection><jtitle>JSME International Journal Series B Fluids and Thermal Engineering</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>OKUI, Hidetaka</au><au>HIRAKI, Hisashi</au><au>PARK, Myeong-Kwan</au><au>OSHIMA, Shuzo</au><au>YAMANE, Ryuichiro</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Control of Pseudo-Shock by Slot Injection</atitle><jtitle>JSME International Journal Series B Fluids and Thermal Engineering</jtitle><date>2002-01-01</date><risdate>2002</risdate><volume>45</volume><issue>1</issue><spage>150</spage><epage>157</epage><pages>150-157</pages><issn>1340-8054</issn><eissn>1347-5371</eissn><abstract>It is well known that the boundary layer separation due to the adverse pressure gradient of the pseudo-shock affects the dynamic feature of the pseudo-shock such as the shape of the first shock, the pressure recovery and the self-induced oscillation. The suppression of the separation is effective to control the interaction between the shock wave and the boundary layer. In this research, the boundary layer control with the slot injection is studied experimentally and numerically. The experiment is carried out in a blow-down supersonic wind tunnel at free stream Mach number of 2.0. The numerical simulation is made with the two-dimensional compressible Navier-Stokes code. In solving the equations, the second-order accurate Harten-Yee's upwind TVD scheme and k-ε turbulence model modified for the compressible flow are used. The results show that the separation is appreciably suppressed and the shape of the first shock is changed, resulting the wall pressure fluctuation to be greatly reduced. Furthermore the total pressure loss is decreased with the low slot height.</abstract><cop>Tokyo</cop><pub>The Japan Society of Mechanical Engineers</pub><doi>10.1299/jsmeb.45.150</doi><tpages>8</tpages><oa>free_for_read</oa></addata></record> |
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| ispartof | JSME International Journal Series B Fluids and Thermal Engineering, 2002, Vol.45(1), pp.150-157 |
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| source | J-STAGE Free; EZB-FREE-00999 freely available EZB journals |
| subjects | Boundary Layer Boundary Layer Control Compressible flows shock and detonation phenomena Exact sciences and technology Flow control Fluid dynamics Fundamental areas of phenomenology (including applications) Passive Control Physics Pseudo-Shock Shock Train Shock Wave Shock-wave interactions and shock effects Shock-wave interactions and shockeffects Supersonic Flow |
| title | Control of Pseudo-Shock by Slot Injection |
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