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dc.contributor.authorShen, Xen_US
dc.contributor.authorAVITAL, Een_US
dc.contributor.authorRezaienia, MAen_US
dc.contributor.authorPaul, Gen_US
dc.contributor.authorAlexander, Ten_US
dc.date.accessioned2016-10-25T15:17:30Z
dc.date.available2016-03-31en_US
dc.date.issued2016-10-02en_US
dc.date.submitted2016-09-23T13:06:21.056Z
dc.identifier.issn1748-3026en_US
dc.identifier.urihttp://qmro.qmul.ac.uk/xmlui/handle/123456789/16067
dc.description.abstractThis article presents computational algorithms for the design, analysis, and optimization of airfoil aerodynamic performance. The prescribed surface curvature distribution blade design (CIRCLE) method is applied to a symmetrical airfoil NACA0012 and a non-symmetrical airfoil E387 to remove their surface curvature and slope-of-curvature discontinuities. Computational fluid dynamics analysis is used to investigate the effects of curvature distribution on aerodynamic performance of the original and modified airfoils. An inviscid–viscid interaction scheme is introduced to predict the positions of laminar separation bubbles. The results are compared with experimental data obtained from tests on the original airfoil geometry. The computed aerodynamic advantages of the modified airfoils are analyzed in different operating conditions. The leading edge singularity of NACA0012 is removed and it is shown that the surface curvature discontinuity affects aerodynamic performance near the stalling angle of attack. The discontinuous slope-of-curvature distribution of E387 results in a larger laminar separation bubble at lower angles of attack and lower Reynolds numbers. It also affects the inherent performance of the airfoil at higher Reynolds numbers. It is shown that at relatively high angles of attack, a continuous slope-of-curvature distribution reduces the skin friction by suppressing both laminar and turbulent separation, and by delaying laminar-turbulent transition. It is concluded that the surface curvature distribution has significant effects on the boundary layer behavior and consequently an improved curvature distribution will lead to higher aerodynamic efficiencyen_US
dc.description.sponsorshipThe author(s) disclosed receipt of the following financial support for the research, authorship, and/or publication of this article: The PhD research of Xiang Shen is funded by China Scholarship Council (CSC)/Queen Mary Joint PhD scholarship.en_US
dc.languageEnglishen_US
dc.publisherMulti-Science Publishingen_US
dc.relation.ispartofJournal of Algorithms and Computational Technologyen_US
dc.rightsCreative Commons CC-BY-NC: This article is distributed under the terms of the Creative Commons Attribution-NonCommercial 3.0 License (http://www. creativecommons.org/licenses/by-nc/3.0/) which permits non-commercial use, reproduction and distribution of the work without further permission provided the original work is attributed as specified on the SAGE and Open Access pages (https://us.sagepub.com/en-us/nam/open-access-at-sage).
dc.subjectThin airfoil theoryen_US
dc.subjectsurface curvatureen_US
dc.subjectboundary layeren_US
dc.subjectaerodynamic efficiencyen_US
dc.titleComputational methods for investigation of surface curvature effects on airfoil boundary layer behavioren_US
dc.typeArticle
dc.rights.holder© The Author(s) 2016
dc.identifier.doi10.1177/1748301816665527en_US
pubs.notesNot knownen_US
pubs.publication-statusPublisheden_US
pubs.publisher-urlhttp://act.sagepub.com/content/early/2016/09/05/1748301816665527.abstracten_US
dcterms.dateAccepted2016-03-31en_US


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