Aerodynamic Load Of An Aircraft With A Highly Elastic Wing

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dc.contributor.authorSchoř, Pavelcs
dc.coverage.issue4cs
dc.coverage.volume57cs
dc.date.issued2017-09-05cs
dc.description.abstractIn this article, a method for calculation of air loads of an aircraft with an elastic wing is presented. The method can predict a redistribution of air loads when the elastic wing deforms. Unlike the traditional Euler or Navier-Stokes CFD to FEM coupling, the method uses 3D panel method as a source of aerodynamic data. This makes the calculation feasible on a typical recent workstation. Due to a short computational time and low hardware demands this method is suitable for both the preliminary design stage and the load evaluation stage. A case study is presented. The study compares a glider wing performing a pull maneuver at both rigid and and elastic state. The study indicates a significant redistribution of air load at the elastic case.en
dc.formattextcs
dc.format.extent272-281cs
dc.format.mimetypeapplication/pdfcs
dc.identifier.citationActa Polytechnica (on-line). 2017, vol. 57, issue 4, p. 272-281.en
dc.identifier.doi10.14311/AP.2017.57.0272cs
dc.identifier.issn1805-2363cs
dc.identifier.other139900cs
dc.identifier.urihttp://hdl.handle.net/11012/70211
dc.language.isoencs
dc.publisherCzech Technical University in Praguecs
dc.relation.ispartofActa Polytechnica (on-line)cs
dc.relation.urihttps://ojs.cvut.cz/ojs/index.php/ap/article/view/4085cs
dc.rightsCreative Commons Attribution 4.0 Internationalcs
dc.rights.accessopenAccesscs
dc.rights.sherpahttp://www.sherpa.ac.uk/romeo/issn/1805-2363/cs
dc.rights.urihttp://creativecommons.org/licenses/by/4.0/cs
dc.subjectaerodynamicsen
dc.subjectpanel methoden
dc.subjectfinite element methoden
dc.subjectwing loaden
dc.titleAerodynamic Load Of An Aircraft With A Highly Elastic Wingen
dc.type.driverarticleen
dc.type.statusPeer-revieweden
dc.type.versionpublishedVersionen
sync.item.dbidVAV-139900en
sync.item.dbtypeVAVen
sync.item.insts2025.02.03 15:47:33en
sync.item.modts2025.01.17 18:41:58en
thesis.grantorVysoké učení technické v Brně. Fakulta strojního inženýrství. Letecký ústavcs
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