Numerical Investigation of Aeroelastic Mode Distribution for Aircraft Wing Model in Subsonic Air Flow
In this paper, the numerical results on two problems originated in aircraft wing modeling have been presented. The first problem is concerned with the approximation to the set of the aeroelastic modes, which are the eigenvalues of a certain boundary-value problem. The affirmative answer is given to...
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| Veröffentlicht in: | Mathematical Problems in Engineering 2010-01, Vol.2010 (1), p.832-853-250 |
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| container_title | Mathematical Problems in Engineering |
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| creator | Shubov, Marianna A. Wineberg, Stephen Holt, Robert |
| description | In this paper, the numerical results on two problems originated in aircraft wing modeling have been presented. The first problem is concerned with the approximation to the set of the aeroelastic modes, which are the eigenvalues of a certain boundary-value problem. The affirmative answer is given to the following question: can the leading asymptotical terms in the analytical formulas be used as reasonably accurate description of the aeroelastic modes? The positive answer means that these leading terms can be used by engineers for practical calculations. The second problem is concerned with the flutter phenomena in aircraft wings in a subsonic, incompressible, inviscid air flow. It has been shown numerically that there exists a pair of the aeroelastic modes whose behavior depends on a speed of an air flow. Namely, when the speed increases, the distance between the modes tends to zero, and at some speed that can be treated as the flutter speed these two modes merge into one double mode. |
| doi_str_mv | 10.1155/2010/879519 |
| format | Article |
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This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.</rights><lds50>peer_reviewed</lds50><oa>free_for_read</oa><woscitedreferencessubscribed>false</woscitedreferencessubscribed><citedby>FETCH-LOGICAL-a437t-edf5ea1a74066b4700d764898a33cd4ed8d19e9cd5dcf8990d4b990b3164b12e3</citedby><cites>FETCH-LOGICAL-a437t-edf5ea1a74066b4700d764898a33cd4ed8d19e9cd5dcf8990d4b990b3164b12e3</cites></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><link.rule.ids>314,780,784,27924,27925</link.rule.ids></links><search><contributor>Balthazar, José</contributor><creatorcontrib>Shubov, Marianna A.</creatorcontrib><creatorcontrib>Wineberg, Stephen</creatorcontrib><creatorcontrib>Holt, Robert</creatorcontrib><title>Numerical Investigation of Aeroelastic Mode Distribution for Aircraft Wing Model in Subsonic Air Flow</title><title>Mathematical Problems in Engineering</title><description>In this paper, the numerical results on two problems originated in aircraft wing modeling have been presented. The first problem is concerned with the approximation to the set of the aeroelastic modes, which are the eigenvalues of a certain boundary-value problem. The affirmative answer is given to the following question: can the leading asymptotical terms in the analytical formulas be used as reasonably accurate description of the aeroelastic modes? The positive answer means that these leading terms can be used by engineers for practical calculations. The second problem is concerned with the flutter phenomena in aircraft wings in a subsonic, incompressible, inviscid air flow. It has been shown numerically that there exists a pair of the aeroelastic modes whose behavior depends on a speed of an air flow. Namely, when the speed increases, the distance between the modes tends to zero, and at some speed that can be treated as the flutter speed these two modes merge into one double mode.</description><subject>Aeroelasticity</subject><subject>Air flow</subject><subject>Aircraft</subject><subject>Boundary value problems</subject><subject>Disk drives</subject><subject>Eigenvalues</subject><subject>Engineering</subject><subject>Fluid flow</subject><subject>Flutter analysis</subject><subject>Incompressible flow</subject><subject>Mathematical analysis</subject><subject>Mathematical models</subject><subject>Numerical analysis</subject><subject>Partial differential equations</subject><subject>Pressure distribution</subject><subject>Studies</subject><subject>Subsonic aircraft</subject><subject>Vibration</subject><subject>Wings (aircraft)</subject><issn>1024-123X</issn><issn>1563-5147</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2010</creationdate><recordtype>article</recordtype><sourceid>RHX</sourceid><sourceid>ABUWG</sourceid><sourceid>AFKRA</sourceid><sourceid>AZQEC</sourceid><sourceid>BENPR</sourceid><sourceid>CCPQU</sourceid><sourceid>DWQXO</sourceid><sourceid>GNUQQ</sourceid><recordid>eNqFkMtKxDAUhosoqKMrXyC4VOqck1vT5aCOCl4GVHRX0ibVSG00bR18e-NUEFducnKS7z-XP0n2EI4QhZhSQJiqLBeYryVbKCRLBfJsPd6B8hQpe9xMtrvuBYCiQLWV2Ovh1QZX6YZctB-2692T7p1via_JzAZvGx3fKnLljSUnruuDK4cVUPtAZi5UQdc9eXDt04ppiGvJ7VB2vo2q-E_mjV_uJBu1bjq7-xMnyf389O74PL28Obs4nl2mmrOsT62phdWoMw5SljwDMJnkKleascpwa5TB3OaVEaaqVZ6D4WU8S4aSl0gtmyT7Y9234N-HuE3x4ofQxpaFEhIUFyAjdDhCVfBdF2xdvAX3qsNngVB821h821iMNkb6YKSfXWv00v0DL0ZYu-B699t9ESmJiHElulLgKmTAKAPA_G-iGI3zsoIKYF-zrYce</recordid><startdate>20100101</startdate><enddate>20100101</enddate><creator>Shubov, Marianna A.</creator><creator>Wineberg, Stephen</creator><creator>Holt, Robert</creator><general>Hindawi Limiteds</general><general>Hindawi Publishing Corporation</general><general>Hindawi Limited</general><scope>188</scope><scope>RHU</scope><scope>RHW</scope><scope>RHX</scope><scope>AAYXX</scope><scope>CITATION</scope><scope>7TB</scope><scope>8FD</scope><scope>8FE</scope><scope>8FG</scope><scope>ABJCF</scope><scope>ABUWG</scope><scope>AFKRA</scope><scope>ARAPS</scope><scope>AZQEC</scope><scope>BENPR</scope><scope>BGLVJ</scope><scope>CCPQU</scope><scope>CWDGH</scope><scope>DWQXO</scope><scope>FR3</scope><scope>GNUQQ</scope><scope>HCIFZ</scope><scope>JQ2</scope><scope>K7-</scope><scope>KR7</scope><scope>L6V</scope><scope>M7S</scope><scope>P5Z</scope><scope>P62</scope><scope>PIMPY</scope><scope>PQEST</scope><scope>PQQKQ</scope><scope>PQUKI</scope><scope>PRINS</scope><scope>PTHSS</scope></search><sort><creationdate>20100101</creationdate><title>Numerical Investigation of Aeroelastic Mode Distribution for Aircraft Wing Model in Subsonic Air Flow</title><author>Shubov, Marianna A. ; Wineberg, Stephen ; Holt, Robert</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-a437t-edf5ea1a74066b4700d764898a33cd4ed8d19e9cd5dcf8990d4b990b3164b12e3</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2010</creationdate><topic>Aeroelasticity</topic><topic>Air flow</topic><topic>Aircraft</topic><topic>Boundary value problems</topic><topic>Disk drives</topic><topic>Eigenvalues</topic><topic>Engineering</topic><topic>Fluid flow</topic><topic>Flutter analysis</topic><topic>Incompressible flow</topic><topic>Mathematical analysis</topic><topic>Mathematical models</topic><topic>Numerical analysis</topic><topic>Partial differential equations</topic><topic>Pressure distribution</topic><topic>Studies</topic><topic>Subsonic aircraft</topic><topic>Vibration</topic><topic>Wings (aircraft)</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Shubov, Marianna A.</creatorcontrib><creatorcontrib>Wineberg, Stephen</creatorcontrib><creatorcontrib>Holt, Robert</creatorcontrib><collection>Airiti Library</collection><collection>Hindawi Publishing Complete</collection><collection>Hindawi Publishing Subscription Journals</collection><collection>Hindawi Publishing Open Access Journals</collection><collection>CrossRef</collection><collection>Mechanical & Transportation Engineering Abstracts</collection><collection>Technology Research Database</collection><collection>ProQuest SciTech Collection</collection><collection>ProQuest Technology Collection</collection><collection>Materials Science & Engineering Collection</collection><collection>ProQuest Central (Alumni Edition)</collection><collection>ProQuest Central UK/Ireland</collection><collection>Advanced Technologies & Aerospace Collection</collection><collection>ProQuest Central Essentials</collection><collection>ProQuest Central</collection><collection>Technology Collection</collection><collection>ProQuest One Community College</collection><collection>Middle East & Africa Database</collection><collection>ProQuest Central Korea</collection><collection>Engineering Research Database</collection><collection>ProQuest Central Student</collection><collection>SciTech Premium Collection</collection><collection>ProQuest Computer Science Collection</collection><collection>Computer Science Database</collection><collection>Civil Engineering Abstracts</collection><collection>ProQuest Engineering Collection</collection><collection>Engineering Database</collection><collection>Advanced Technologies & Aerospace Database</collection><collection>ProQuest Advanced Technologies & Aerospace Collection</collection><collection>Access via ProQuest (Open Access)</collection><collection>ProQuest One Academic Eastern Edition (DO NOT USE)</collection><collection>ProQuest One Academic</collection><collection>ProQuest One Academic UKI Edition</collection><collection>ProQuest Central China</collection><collection>Engineering Collection</collection><jtitle>Mathematical Problems in Engineering</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>Shubov, Marianna A.</au><au>Wineberg, Stephen</au><au>Holt, Robert</au><au>Balthazar, José</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Numerical Investigation of Aeroelastic Mode Distribution for Aircraft Wing Model in Subsonic Air Flow</atitle><jtitle>Mathematical Problems in Engineering</jtitle><date>2010-01-01</date><risdate>2010</risdate><volume>2010</volume><issue>1</issue><spage>832</spage><epage>853-250</epage><pages>832-853-250</pages><issn>1024-123X</issn><eissn>1563-5147</eissn><abstract>In this paper, the numerical results on two problems originated in aircraft wing modeling have been presented. The first problem is concerned with the approximation to the set of the aeroelastic modes, which are the eigenvalues of a certain boundary-value problem. The affirmative answer is given to the following question: can the leading asymptotical terms in the analytical formulas be used as reasonably accurate description of the aeroelastic modes? The positive answer means that these leading terms can be used by engineers for practical calculations. The second problem is concerned with the flutter phenomena in aircraft wings in a subsonic, incompressible, inviscid air flow. It has been shown numerically that there exists a pair of the aeroelastic modes whose behavior depends on a speed of an air flow. Namely, when the speed increases, the distance between the modes tends to zero, and at some speed that can be treated as the flutter speed these two modes merge into one double mode.</abstract><cop>New York</cop><pub>Hindawi Limiteds</pub><doi>10.1155/2010/879519</doi><tpages>22</tpages><oa>free_for_read</oa></addata></record> |
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| subjects | Aeroelasticity Air flow Aircraft Boundary value problems Disk drives Eigenvalues Engineering Fluid flow Flutter analysis Incompressible flow Mathematical analysis Mathematical models Numerical analysis Partial differential equations Pressure distribution Studies Subsonic aircraft Vibration Wings (aircraft) |
| title | Numerical Investigation of Aeroelastic Mode Distribution for Aircraft Wing Model in Subsonic Air Flow |
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