Large eddy simulation of a heaving wing on the cusp of transition to turbulence
Large eddy simulation of a heaving wing on the cusp of transition to turbulence
Simulations of the flow over a heaving NACA 0012 wing are conducted to study the separated flow phenomena for a pre-stall and post-stall wing condition. An extensively validated high fidelity large-eddy simulation (LES) approach is used to examine the unsteady aerodynamic loads and flow structures at Reynolds number Re c = 2×10 4 based on the chord. We consider the effect of varying reduced frequencies from k =0.47-0.94 for a chord-normalized peak-to-peak amplitude of A/c=0.5 and angles of attack of 5 ◦ and 15 ◦ , representing pre-stall and post-stall conditions respectively. Comparison to experiment shows good agreement for the phase-averaged lift, drag and momentsof the heaving wing. Characteristic phenomena of dynamic stall are analysed with emphasis on the leading edge vortex (LEV) development. A series of instantaneous spanwise vorticity plots show significant spanwise perturbations in the reverse flow region that develops over the suction surface during the start of the downstroke, giving rise to instabilities in the detached shear layer. The instabilities are associated with the first occurrence of turbulence near the wing surface.
Dynamic stall, Large-eddy simulations, Oscillating wing, Transition, Instability
64-77
Badoe, Charles
b0d47aa4-aa66-4621-86dd-d0c7e2bdf3b5
Xie, Zheng-Tong
98ced75d-5617-4c2d-b20f-7038c54f4ff0
Sandham, Neil
0024d8cd-c788-4811-a470-57934fbdcf97
30 April 2019
Badoe, Charles
b0d47aa4-aa66-4621-86dd-d0c7e2bdf3b5
Xie, Zheng-Tong
98ced75d-5617-4c2d-b20f-7038c54f4ff0
Sandham, Neil
0024d8cd-c788-4811-a470-57934fbdcf97
Badoe, Charles, Xie, Zheng-Tong and Sandham, Neil
(2019)
Large eddy simulation of a heaving wing on the cusp of transition to turbulence.
Computers & Fluids, 184, .
(doi:10.1016/j.compfluid.2019.03.023).
Abstract
Simulations of the flow over a heaving NACA 0012 wing are conducted to study the separated flow phenomena for a pre-stall and post-stall wing condition. An extensively validated high fidelity large-eddy simulation (LES) approach is used to examine the unsteady aerodynamic loads and flow structures at Reynolds number Re c = 2×10 4 based on the chord. We consider the effect of varying reduced frequencies from k =0.47-0.94 for a chord-normalized peak-to-peak amplitude of A/c=0.5 and angles of attack of 5 ◦ and 15 ◦ , representing pre-stall and post-stall conditions respectively. Comparison to experiment shows good agreement for the phase-averaged lift, drag and momentsof the heaving wing. Characteristic phenomena of dynamic stall are analysed with emphasis on the leading edge vortex (LEV) development. A series of instantaneous spanwise vorticity plots show significant spanwise perturbations in the reverse flow region that develops over the suction surface during the start of the downstroke, giving rise to instabilities in the detached shear layer. The instabilities are associated with the first occurrence of turbulence near the wing surface.
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Submitted date: 21 May 2018
Accepted/In Press date: 22 March 2019
e-pub ahead of print date: 30 March 2019
Published date: 30 April 2019
Keywords:
Dynamic stall, Large-eddy simulations, Oscillating wing, Transition, Instability
Identifiers
Local EPrints ID: 421175
URI: http://eprints.soton.ac.uk/id/eprint/421175
ISSN: 0045-7930
PURE UUID: 2fe4e51a-6898-4804-b8bc-b44bb94eea78
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Date deposited: 24 May 2018 16:30
Last modified: 16 Mar 2024 06:40
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Author:
Neil Sandham
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