Active Control of Flow around NACA 0015 Airfoil by Using DBD Plasma Actuator

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dc.contributor.authorAkansu, Y. E.
dc.contributor.authorKarakaya, F.
dc.contributor.authorSanlisoy, A.
dc.contributor.editorDancova, P
dc.contributor.editorNovonty, P
dc.date.accessioned2019-08-01T13:38:39Z
dc.date.available2019-08-01T13:38:39Z
dc.date.issued2013
dc.departmentNiğde ÖHÜ
dc.description7th International Conference on Experimental Fluid Mechanics (EFM) -- NOV 20-23, 2012 -- Tech Univ Liberec (TU Liberec), Hradec Kralove, CZECH REPUBLIC
dc.description.abstractIn this study, effect of plasma actuator on a flat plate and manipulation of flow separation on NACA0015 airfoil with plasma actuator at low Reynolds numbers were experimentally investigated. In the first section of the study, plasma actuator which consists of positive and grounded electrode couple and dielectric layer, located on a flat plate was actuated at different frequencies and peak to peak voltages in range of 3-5 kHz and 6-12 kV respectively. The induced air flow velocity on the surface of flat plate was measured by pitot tube at different locations behind the actuator. The influence of dielectric thickness and unsteady actuation with duty cycle was also examined. In the second section, the effect of plasma actuator on NACA0015 airfoil was studied at Reynolds number 15000 and 30000. Four plasma actuators were placed at x/C = 0.1, 0.3, 0.5 and 0.9, and different electrode combinations were activated by sinusoidal signal. Flow visualizations were done when the attack angles were 0 degrees, 5 degrees, 10 degrees, 15 degrees and 20 degrees. The results indicate that up to the 15 degrees attack angle, the separated flow was reattached by plasma actuator at 12kV peak to peak voltage and 4 kHz frequency. However, 12 kV(pp) voltage was insufficient to reattach the flow at 20 angle of attack. The separated flow could be reattached by increasing the voltage up to 13 kV. Lift coefficient was also increased by the manipulated flow over the airfoil. Results showed that even high attack angles, the actuators can control the flow separation and prevent the airfoil from stall at low Reynolds numbers.
dc.description.sponsorshipDantec Dynam GmbH, Kamax Holding, LENAM s r o, MIT s r o, SPECION s r o
dc.description.sponsorshipScientific and Technological Research Council of Turkey (TUBITAK) [110M056]
dc.description.sponsorshipThe authors would like to acknowledge the financial support of this work by the Scientific and Technological Research Council of Turkey (TUBITAK) under the Contract Number of 110M056.
dc.identifier.doi10.1051/epjconf/20134501008
dc.identifier.isbn978-80-7372-912-7
dc.identifier.issn2100-014X
dc.identifier.scopus2-s2.0-84881624658
dc.identifier.scopusqualityN/A
dc.identifier.urihttps://dx.doi.org/10.1051/epjconf/20134501008
dc.identifier.urihttps://hdl.handle.net/11480/4468
dc.identifier.volume45
dc.identifier.wosWOS:000319932200008
dc.identifier.wosqualityN/A
dc.indekslendigikaynakWeb of Science
dc.indekslendigikaynakScopus
dc.institutionauthor[0-Belirlenecek]
dc.language.isoen
dc.publisherE D P SCIENCES
dc.relation.ispartofEFM12 - EXPERIMENTAL FLUID MECHANICS 2012
dc.relation.ispartofseriesEPJ Web of Conferences
dc.relation.publicationcategoryKonferans Öğesi - Uluslararası - Kurum Öğretim Elemanı
dc.rightsinfo:eu-repo/semantics/openAccess
dc.titleActive Control of Flow around NACA 0015 Airfoil by Using DBD Plasma Actuator
dc.typeConference Object

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