Comparison of the Linear and Spanwise-Segmented DBD Plasma Actuators on Flow Control Around a NACA0015 Airfoil

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dc.authoridYAVUZ, Hakan/0000-0002-6166-0921
dc.contributor.authorAkbiyik, Hurrem
dc.contributor.authorYavuz, Hakan
dc.contributor.authorAkansu, Yahya Erkan
dc.date.accessioned2024-11-07T13:31:42Z
dc.date.available2024-11-07T13:31:42Z
dc.date.issued2017
dc.departmentNiğde Ömer Halisdemir Üniversitesi
dc.description.abstractIn this paper, linear and spanwise-segmented plasma actuator implementations as well as base airfoil with no plasma cases are presented. These approaches are used to control the flow around a NACA0015 airfoil. The experiments were conducted in a wind tunnel at Reynolds number of 3.6x10(4). The plasma actuators mounted on the leading edge of the airfoil at chord position of 0.1 (x/C). The electrical parameters used for the plasma generating device are set to constant values of 6-kV(pp) applied voltage and 3.5-kHz excitation frequency. It is observed that the use of spanwise-segmented plasma actuators converts the 2-D flow structure around the airfoil into 3-D forcing flow structure. The change of the wake region width of the airfoil is visualized by using the smoke-wire method. The flow visualization is performed at attack angles of 0 degrees, 5 degrees, 10 degrees, and 15 degrees. In addition, necessary measurements are also made to determine drag and lift forces. A comparative study on the drag and lift forces for the NACA0015 airfoil is performed. As a part of the conclusions, linear and spanwise-segmented plasma actuator implementations as well as base airfoil with no plasma cases are compared and related results on flow control are presented.
dc.identifier.doi10.1109/TPS.2017.2754949
dc.identifier.endpage2921
dc.identifier.issn0093-3813
dc.identifier.issn1939-9375
dc.identifier.issue11
dc.identifier.scopus2-s2.0-85030750035
dc.identifier.scopusqualityQ3
dc.identifier.startpage2913
dc.identifier.urihttps://doi.org/10.1109/TPS.2017.2754949
dc.identifier.urihttps://hdl.handle.net/11480/14988
dc.identifier.volume45
dc.identifier.wosWOS:000414688600002
dc.identifier.wosqualityQ3
dc.indekslendigikaynakWeb of Science
dc.indekslendigikaynakScopus
dc.language.isoen
dc.publisherIEEE-Inst Electrical Electronics Engineers Inc
dc.relation.ispartofIeee Transactions on Plasma Science
dc.relation.publicationcategoryMakale - Uluslararası Hakemli Dergi - Kurum Öğretim Elemanı
dc.rightsinfo:eu-repo/semantics/closedAccess
dc.snmzKA_20241106
dc.subjectActuators
dc.subjectaircraft
dc.subjectflow control
dc.subjectforce measurement
dc.subjectplasma applications
dc.titleComparison of the Linear and Spanwise-Segmented DBD Plasma Actuators on Flow Control Around a NACA0015 Airfoil
dc.typeArticle

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