Vortex dynamics of a finite-aspect-ratio plunging wing

Azar Eslam Panah, James M. Akkala, James H.J. Buchholz

Research output: Chapter in Book/Report/Conference proceedingConference contribution

2 Citations (Scopus)

Abstract

The structure and dynamics of the leading-edge vortex (LEV) were investigated for plunging finite-aspect-ratio wings at a chord Reynolds number of 10,000 while varying aspect ratio and root boundary condition. Stereoscopic particle image velocimetry (SPIV) measurements were used to characterize LEV dynamics and interactions with the plate in multiple chordwise planes. The relationship between the vorticity field and the spanwise flow field over the wing, and the influence of root boundary conditions on these quantities has been investigated. The viscous symmetry plane was found to influence this flow field, in comparison to other studies,1-3 by influencing tilting of the LEV near the symmetry wall, and introducing a corewise root-to-tip flow near the symmetry plane. Modifications in the root boundary conditions were found to significantly affect this. LEV circulations for the different aspect ratio plates were also compared. At the bottom of the downstroke, the maximum circulation was found at the middle of the semi-span in each case. The circulation of the sAR = 2 wing was found to significantly exceed that of the sAR = 1 wing and, surprisingly, the maximum circulation value was found to be independent of root boundary conditions for the sAR = 2 case and also closely matched that of the quasi-2D case.

Original languageEnglish (US)
Title of host publication51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013
StatePublished - Aug 19 2013
Event51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013 - Grapevine, TX, United States
Duration: Jan 7 2013Jan 10 2013

Publication series

Name51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013

Other

Other51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013
CountryUnited States
CityGrapevine, TX
Period1/7/131/10/13

Fingerprint

leading edges
wings
vortex
aspect ratio
Aspect ratio
Vortex flow
Boundary conditions
vortices
boundary conditions
boundary condition
symmetry
Flow fields
flow distribution
flow field
particle image velocimetry
Vorticity
Velocity measurement
vorticity
Reynolds number
interactions

All Science Journal Classification (ASJC) codes

  • Space and Planetary Science
  • Aerospace Engineering

Cite this

Eslam Panah, A., Akkala, J. M., & Buchholz, J. H. J. (2013). Vortex dynamics of a finite-aspect-ratio plunging wing. In 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013 (51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013).
Eslam Panah, Azar ; Akkala, James M. ; Buchholz, James H.J. / Vortex dynamics of a finite-aspect-ratio plunging wing. 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013. 2013. (51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013).
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abstract = "The structure and dynamics of the leading-edge vortex (LEV) were investigated for plunging finite-aspect-ratio wings at a chord Reynolds number of 10,000 while varying aspect ratio and root boundary condition. Stereoscopic particle image velocimetry (SPIV) measurements were used to characterize LEV dynamics and interactions with the plate in multiple chordwise planes. The relationship between the vorticity field and the spanwise flow field over the wing, and the influence of root boundary conditions on these quantities has been investigated. The viscous symmetry plane was found to influence this flow field, in comparison to other studies,1-3 by influencing tilting of the LEV near the symmetry wall, and introducing a corewise root-to-tip flow near the symmetry plane. Modifications in the root boundary conditions were found to significantly affect this. LEV circulations for the different aspect ratio plates were also compared. At the bottom of the downstroke, the maximum circulation was found at the middle of the semi-span in each case. The circulation of the sAR = 2 wing was found to significantly exceed that of the sAR = 1 wing and, surprisingly, the maximum circulation value was found to be independent of root boundary conditions for the sAR = 2 case and also closely matched that of the quasi-2D case.",
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Eslam Panah, A, Akkala, JM & Buchholz, JHJ 2013, Vortex dynamics of a finite-aspect-ratio plunging wing. in 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013. 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013, 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013, Grapevine, TX, United States, 1/7/13.

Vortex dynamics of a finite-aspect-ratio plunging wing. / Eslam Panah, Azar; Akkala, James M.; Buchholz, James H.J.

51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013. 2013. (51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013).

Research output: Chapter in Book/Report/Conference proceedingConference contribution

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N2 - The structure and dynamics of the leading-edge vortex (LEV) were investigated for plunging finite-aspect-ratio wings at a chord Reynolds number of 10,000 while varying aspect ratio and root boundary condition. Stereoscopic particle image velocimetry (SPIV) measurements were used to characterize LEV dynamics and interactions with the plate in multiple chordwise planes. The relationship between the vorticity field and the spanwise flow field over the wing, and the influence of root boundary conditions on these quantities has been investigated. The viscous symmetry plane was found to influence this flow field, in comparison to other studies,1-3 by influencing tilting of the LEV near the symmetry wall, and introducing a corewise root-to-tip flow near the symmetry plane. Modifications in the root boundary conditions were found to significantly affect this. LEV circulations for the different aspect ratio plates were also compared. At the bottom of the downstroke, the maximum circulation was found at the middle of the semi-span in each case. The circulation of the sAR = 2 wing was found to significantly exceed that of the sAR = 1 wing and, surprisingly, the maximum circulation value was found to be independent of root boundary conditions for the sAR = 2 case and also closely matched that of the quasi-2D case.

AB - The structure and dynamics of the leading-edge vortex (LEV) were investigated for plunging finite-aspect-ratio wings at a chord Reynolds number of 10,000 while varying aspect ratio and root boundary condition. Stereoscopic particle image velocimetry (SPIV) measurements were used to characterize LEV dynamics and interactions with the plate in multiple chordwise planes. The relationship between the vorticity field and the spanwise flow field over the wing, and the influence of root boundary conditions on these quantities has been investigated. The viscous symmetry plane was found to influence this flow field, in comparison to other studies,1-3 by influencing tilting of the LEV near the symmetry wall, and introducing a corewise root-to-tip flow near the symmetry plane. Modifications in the root boundary conditions were found to significantly affect this. LEV circulations for the different aspect ratio plates were also compared. At the bottom of the downstroke, the maximum circulation was found at the middle of the semi-span in each case. The circulation of the sAR = 2 wing was found to significantly exceed that of the sAR = 1 wing and, surprisingly, the maximum circulation value was found to be independent of root boundary conditions for the sAR = 2 case and also closely matched that of the quasi-2D case.

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Eslam Panah A, Akkala JM, Buchholz JHJ. Vortex dynamics of a finite-aspect-ratio plunging wing. In 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013. 2013. (51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013).