Effect of Yaw Angles on Aerodynamics of a Slender Delta Wing

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dc.authoridSahin, Besir/0000-0003-0671-0890
dc.authoridKarasu, Ilyas/0000-0003-3138-6236
dc.contributor.authorKarasu, Ilyas
dc.contributor.authorSahin, Besir
dc.contributor.authorTasci, M. Oguz
dc.contributor.authorAkilli, Huseyin
dc.date.accessioned2025-01-06T17:37:29Z
dc.date.available2025-01-06T17:37:29Z
dc.date.issued2019
dc.description.abstractIn the present investigation, flow structures over a slender delta wing with a 70 degrees sweep angle, ? at an angle of attack, alpha of 30 degrees, and under the variation of yaw angles within the range of 0 degrees <=beta <= 20 degrees were investigated experimentally. To analyze the flow structure qualitatively and quantitatively, dye visualizations, surface oil visualizations, surface pressure measurements, and velocity measurements using the stereo particle image velocimetry (PIV) were conducted at Reynolds numbers of Re=2x10(4) and Re=1x10(5). Instantaneous and time-averaged flow data were analyzed to demonstrate the effect of yaw angle (beta) on the alterations of leading-edge vortex formation, vortex breakdown, and also vortical flow structures over the wing surface. Time-averaged distributions of streamwise velocity component, u over bar /U, transverse velocity component v over bar /U, patterns of streamline, psi, and distributions of turbulent kinetic energy TKE/U2 were presented to reveal the physics of flow structures under yaw angle (beta) variations. Distribution of pressure coefficients, (-Cp) at various x/c and y/c locations were also presented. The experimental results demonstrated that the variation of yaw angles (beta) has a strong effect on the alterations of the flow structure, the leading-edge vortex formation, and its breakdown. An increase of yaw angle (beta) causes asymmetrical flow structures and hence expands this asymmetrical flow domain further. (c) 2019 American Society of Civil Engineers.
dc.description.sponsorshipScientific and Technological Research Council of Turkey (TuBTAK) [114M497]; Cukurova University Scientific Research Unit [MMF2013D9]
dc.description.sponsorshipThe Scientific and Technological Research Council of Turkey (TuBTAK) under contract number of 114M497 and Cukurova University Scientific Research Unit under contract number of MMF2013D9 supported this investigation. The authors are grateful to Erciyes University Department of Energy Systems Engineering for allowing the use of the wind tunnel.
dc.identifier.doi10.1061/(ASCE)AS.1943-5525.0001066
dc.identifier.issn0893-1321
dc.identifier.issn1943-5525
dc.identifier.issue5
dc.identifier.scopus2-s2.0-85067864595
dc.identifier.scopusqualityQ2
dc.identifier.urihttps://doi.org/10.1061/(ASCE)AS.1943-5525.0001066
dc.identifier.urihttps://hdl.handle.net/20.500.14669/2222
dc.identifier.volume32
dc.identifier.wosWOS:000475509500024
dc.identifier.wosqualityQ2
dc.indekslendigikaynakWeb of Science
dc.indekslendigikaynakScopus
dc.language.isoen
dc.publisherAsce-Amer Soc Civil Engineers
dc.relation.ispartofJournal of Aerospace Engineering
dc.relation.publicationcategoryMakale - Uluslararası Hakemli Dergi - Kurum Öğretim Elemanı
dc.rightsinfo:eu-repo/semantics/closedAccess
dc.snmzKA_20241211
dc.subjectDelta wing
dc.subjectStereo particle image velocimetry (PIV)
dc.subjectVortex breakdown
dc.subjectYaw angle
dc.titleEffect of Yaw Angles on Aerodynamics of a Slender Delta Wing
dc.typeArticle

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