An experimental study of acoustic disturbances effect on laminar separation bubble and transition over an aerofoil at low reynolds number

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dc.authorscopusid55805951800
dc.authorscopusid24400712600
dc.authorscopusid57203990469
dc.authorscopusid54977980200
dc.contributor.authorHakan Açikel, H.
dc.contributor.authorSerdar Genç, M.
dc.contributor.authorTu?rul Akpolat, M.
dc.contributor.authorKarasu, Ilyas
dc.date.accessioned2024-09-19T15:41:15Z
dc.date.available2024-09-19T15:41:15Z
dc.date.issued2012
dc.departmentHatay Mustafa Kemal Üniversitesien_US
dc.descriptionAmerican Institute of Aeronautics and Astronautics (AIAA)en_US
dc.description6th AIAA Flow Control Conference 2012 -- 25 June 2012 through 28 June 2012 -- New Orleans, LA -- 98167en_US
dc.description.abstractIn this study, the effect of parallel acoustic excitation on laminar separation bubble over NACA2415 aerofoil and stall characteristics of the aerofoil were investigated at Re=50x103 and at various angles of attack. A sound source connected to a signal generator and an audio amplifier was placed in front of the wind tunnel to be parallel to the aerofoil. The amplitude of the sinusoidal sound wave was kept constant at 60 dB to determine the effects of varying frequencies from 70 Hz to 1100 Hz. In the experiments, an external three component load-cell system for force measurements, a scanivalve unit and a pressure transducer for pressure measurements and smoke-wire technique for flow visualization were used. The pressure measurement experiments showed that at the range of 200 Hz to 850 Hz the separated flow was reattached at the angle of attack of 15° and the laminar separation bubble was shortened at the angle of attack of 8° The shortened laminar separation bubble was seen clearly from some-wire flow visualization photos. Furthermore, the stall angle was delayed from ?s=12° to ?s=16° and CLmax was increased from 1.2 to 1.56 with acoustic excitation of 350 Hz. © 2012 by the American Institute of Aeronautics and Astronautics, Inc.en_US
dc.identifier.isbn978-162410188-5
dc.identifier.scopus2-s2.0-84880781282en_US
dc.identifier.scopusqualityN/Aen_US
dc.identifier.urihttps://hdl.handle.net/20.500.12483/14128
dc.indekslendigikaynakScopusen_US
dc.language.isoenen_US
dc.relation.ispartof6th AIAA Flow Control Conference 2012en_US
dc.relation.publicationcategoryKonferans Öğesi - Uluslararası - Kurum Öğretim Elemanıen_US
dc.rightsinfo:eu-repo/semantics/closedAccessen_US
dc.subjectAcoustic wave transmissionen_US
dc.subjectAngle of attacken_US
dc.subjectAudio frequency amplifiersen_US
dc.subjectFlow controlen_US
dc.subjectLaminar flowen_US
dc.subjectPressure measurementen_US
dc.subjectReynolds numberen_US
dc.subjectWireen_US
dc.subjectAcoustic disturbancesen_US
dc.subjectAcoustic excitationen_US
dc.subjectAngles of attacken_US
dc.subjectAudio amplifiersen_US
dc.subjectExperimental studiesen_US
dc.subjectLaminar separation bubbleen_US
dc.subjectLow Reynolds numberen_US
dc.subjectMeasurement experimentsen_US
dc.subjectFlow visualizationen_US
dc.titleAn experimental study of acoustic disturbances effect on laminar separation bubble and transition over an aerofoil at low reynolds numberen_US
dc.typeConference Objecten_US

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