Nonlinear Aeroelastic Characteristics of a Laminated Composite Wing Considering Compressible Shock Wave Effects
In this study, advanced computational analysis system for nonlinear static aeroelastic problems has been successfully developed by the composite structure (FEM)-fluid (CFD) combined method with internal iteration steps. Major focus of the present study is to investigate the static aeroelastic charac...
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| Veröffentlicht in: | Key engineering materials 2007-03, Vol.334-335, p.481-484 |
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| container_title | Key engineering materials |
| container_volume | 334-335 |
| creator | Lee, Seok Soon Kim, Dong Hyun Oh, Il Kwon Kim, Hyun Jung |
| description | In this study, advanced computational analysis system for nonlinear static aeroelastic
problems has been successfully developed by the composite structure (FEM)-fluid (CFD) combined
method with internal iteration steps. Major focus of the present study is to investigate the static
aeroelastic characteristics of laminated composite wings including the strong normal shock waves in
the transonic and low-supersonic flow regions. The results importantly indicate that the effect of
airfoil camber on the load distribution of laminated composite wing models can be nonlinear due to
the variation of ply orientations. |
| doi_str_mv | 10.4028/www.scientific.net/KEM.334-335.481 |
| format | Article |
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problems has been successfully developed by the composite structure (FEM)-fluid (CFD) combined
method with internal iteration steps. Major focus of the present study is to investigate the static
aeroelastic characteristics of laminated composite wings including the strong normal shock waves in
the transonic and low-supersonic flow regions. The results importantly indicate that the effect of
airfoil camber on the load distribution of laminated composite wing models can be nonlinear due to
the variation of ply orientations.</description><identifier>ISSN: 1013-9826</identifier><identifier>ISSN: 1662-9795</identifier><identifier>EISSN: 1662-9795</identifier><identifier>DOI: 10.4028/www.scientific.net/KEM.334-335.481</identifier><language>eng</language><publisher>Trans Tech Publications Ltd</publisher><ispartof>Key engineering materials, 2007-03, Vol.334-335, p.481-484</ispartof><rights>2007 Trans Tech Publications Ltd</rights><lds50>peer_reviewed</lds50><woscitedreferencessubscribed>false</woscitedreferencessubscribed><cites>FETCH-LOGICAL-c236t-57535d3bfe33362ded90186a810bc7a4680199ec2a2278e86e3b333782b42a233</cites></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Uhttps://www.scientific.net/Image/TitleCover/57?width=600</thumbnail><link.rule.ids>314,780,784,27924,27925</link.rule.ids></links><search><creatorcontrib>Lee, Seok Soon</creatorcontrib><creatorcontrib>Kim, Dong Hyun</creatorcontrib><creatorcontrib>Oh, Il Kwon</creatorcontrib><creatorcontrib>Kim, Hyun Jung</creatorcontrib><title>Nonlinear Aeroelastic Characteristics of a Laminated Composite Wing Considering Compressible Shock Wave Effects</title><title>Key engineering materials</title><description>In this study, advanced computational analysis system for nonlinear static aeroelastic
problems has been successfully developed by the composite structure (FEM)-fluid (CFD) combined
method with internal iteration steps. Major focus of the present study is to investigate the static
aeroelastic characteristics of laminated composite wings including the strong normal shock waves in
the transonic and low-supersonic flow regions. The results importantly indicate that the effect of
airfoil camber on the load distribution of laminated composite wing models can be nonlinear due to
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problems has been successfully developed by the composite structure (FEM)-fluid (CFD) combined
method with internal iteration steps. Major focus of the present study is to investigate the static
aeroelastic characteristics of laminated composite wings including the strong normal shock waves in
the transonic and low-supersonic flow regions. The results importantly indicate that the effect of
airfoil camber on the load distribution of laminated composite wing models can be nonlinear due to
the variation of ply orientations.</abstract><pub>Trans Tech Publications Ltd</pub><doi>10.4028/www.scientific.net/KEM.334-335.481</doi><tpages>4</tpages></addata></record> |
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| title | Nonlinear Aeroelastic Characteristics of a Laminated Composite Wing Considering Compressible Shock Wave Effects |
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