Investigation of Unswept Normal Shock Wave/Turbulent-Boundary-Layer Interaction Control
An analytical model for the unswept normal shock wave/turbulent-boundary-layer interaction control using an upstream and downstream unimorph piezoelectric flap actuator has been proposed. The amount of flap deflection controls the bleed/suction rate through a plenum chamber. The cavity allows rapid...
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| Veröffentlicht in: | Journal of aircraft 2009-09, Vol.46 (5), p.1634-1641 |
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| container_title | Journal of aircraft |
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| creator | Couldrick, Jonathan S Gai, Sudhir L Milthorpe, John F Shankar, Krishna |
| description | An analytical model for the unswept normal shock wave/turbulent-boundary-layer interaction control using an upstream and downstream unimorph piezoelectric flap actuator has been proposed. The amount of flap deflection controls the bleed/suction rate through a plenum chamber. The cavity allows rapid thickening of the boundary layer approaching a normal shock wave, which splits into a series of weaker shocks forming a lambda shock foot, leading to a reduction in the wave drag. The analysis provides an understanding of the control influences produced in an experimental investigation of an unswept normal shock wave/turbulent-boundary-layer interaction at a Mach number of 1.5. It has also been validated by application to the normal shock wave/boundary-layer interaction control system using mesoflaps for aeroelastic transpiration described in previous transonic/supersonic shock wave/boundary-layer interaction studies. [PUBLICATION ABSTRACT] |
| doi_str_mv | 10.2514/1.42104 |
| format | Article |
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The amount of flap deflection controls the bleed/suction rate through a plenum chamber. The cavity allows rapid thickening of the boundary layer approaching a normal shock wave, which splits into a series of weaker shocks forming a lambda shock foot, leading to a reduction in the wave drag. The analysis provides an understanding of the control influences produced in an experimental investigation of an unswept normal shock wave/turbulent-boundary-layer interaction at a Mach number of 1.5. It has also been validated by application to the normal shock wave/boundary-layer interaction control system using mesoflaps for aeroelastic transpiration described in previous transonic/supersonic shock wave/boundary-layer interaction studies. 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The amount of flap deflection controls the bleed/suction rate through a plenum chamber. The cavity allows rapid thickening of the boundary layer approaching a normal shock wave, which splits into a series of weaker shocks forming a lambda shock foot, leading to a reduction in the wave drag. The analysis provides an understanding of the control influences produced in an experimental investigation of an unswept normal shock wave/turbulent-boundary-layer interaction at a Mach number of 1.5. It has also been validated by application to the normal shock wave/boundary-layer interaction control system using mesoflaps for aeroelastic transpiration described in previous transonic/supersonic shock wave/boundary-layer interaction studies. [PUBLICATION ABSTRACT]</description><subject>Aircraft</subject><subject>Boundary layer and shear turbulence</subject><subject>Compressible flows; shock and detonation phenomena</subject><subject>Control</subject><subject>Exact sciences and technology</subject><subject>Flow control</subject><subject>Fluid dynamics</subject><subject>Fundamental areas of phenomenology (including applications)</subject><subject>Physics</subject><subject>Shock-wave interactions and shock effects</subject><subject>Turbulence</subject><subject>Turbulent flows, convection, and heat transfer</subject><issn>0021-8669</issn><issn>1533-3868</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2009</creationdate><recordtype>article</recordtype><recordid>eNpt0F1PHCEUBmBiauJWm_6FSdOP9GL0MMwAc6mbfmyy0Ytu4yU5y4COZWEFxtZ_X3RNm7RecRIe3sM5hLymcNx0tD2hx21Dod0jM9oxVjPJ5QsyA2hoLTnvD8jLlG4AQIIQM3K58Hcm5fEK8xh8FWz13aefZpur8xA36Kpv10H_qC7xzpysprienPG5PguTHzDe10u8N7Fa-Gwi6seEefA5BndE9i26ZF49nYdk9fnTav61Xl58WcxPlzUywXM99IPQ0KLUHeuNbihHRAtWd1AqZtiamTVnrINOrK1goh-g04zrvtXQC3ZI3u9itzHcTmUQtRmTNs6hN2FKqjyktJddgW_-gTdhir58TTUgOJWStQV92CEdQ0rRWLWN46bMqSioh-Uqqh6XW-S7pzhMGp2N6PWY_vCmAaCSN8W93TkcEf-2_D_u47Nsd622g1V2ci6bX5n9Bsfxklc</recordid><startdate>20090901</startdate><enddate>20090901</enddate><creator>Couldrick, Jonathan S</creator><creator>Gai, Sudhir L</creator><creator>Milthorpe, John F</creator><creator>Shankar, Krishna</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><scope>U9A</scope></search><sort><creationdate>20090901</creationdate><title>Investigation of Unswept Normal Shock Wave/Turbulent-Boundary-Layer Interaction Control</title><author>Couldrick, Jonathan S ; Gai, Sudhir L ; Milthorpe, John F ; Shankar, Krishna</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-a376t-d9d7c04a8c539ec216aaaf0fc506aa3e3b3eb6335057bf7379d05c36c94c0973</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2009</creationdate><topic>Aircraft</topic><topic>Boundary layer and shear turbulence</topic><topic>Compressible flows; shock and detonation phenomena</topic><topic>Control</topic><topic>Exact sciences and technology</topic><topic>Flow control</topic><topic>Fluid dynamics</topic><topic>Fundamental areas of phenomenology (including applications)</topic><topic>Physics</topic><topic>Shock-wave interactions and shock effects</topic><topic>Turbulence</topic><topic>Turbulent flows, convection, and heat transfer</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Couldrick, Jonathan S</creatorcontrib><creatorcontrib>Gai, Sudhir L</creatorcontrib><creatorcontrib>Milthorpe, John F</creatorcontrib><creatorcontrib>Shankar, Krishna</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>Journal of aircraft</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>Couldrick, Jonathan S</au><au>Gai, Sudhir L</au><au>Milthorpe, John F</au><au>Shankar, Krishna</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Investigation of Unswept Normal Shock Wave/Turbulent-Boundary-Layer Interaction Control</atitle><jtitle>Journal of aircraft</jtitle><date>2009-09-01</date><risdate>2009</risdate><volume>46</volume><issue>5</issue><spage>1634</spage><epage>1641</epage><pages>1634-1641</pages><issn>0021-8669</issn><eissn>1533-3868</eissn><coden>JAIRAM</coden><abstract>An analytical model for the unswept normal shock wave/turbulent-boundary-layer interaction control using an upstream and downstream unimorph piezoelectric flap actuator has been proposed. 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| ispartof | Journal of aircraft, 2009-09, Vol.46 (5), p.1634-1641 |
| issn | 0021-8669 1533-3868 |
| language | eng |
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| source | Alma/SFX Local Collection |
| subjects | Aircraft Boundary layer and shear turbulence Compressible flows shock and detonation phenomena Control Exact sciences and technology Flow control Fluid dynamics Fundamental areas of phenomenology (including applications) Physics Shock-wave interactions and shock effects Turbulence Turbulent flows, convection, and heat transfer |
| title | Investigation of Unswept Normal Shock Wave/Turbulent-Boundary-Layer Interaction Control |
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