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Direct numerical simulations of transonic flow around an airfoil at moderate Reynolds numbers

Direct numerical simulations of transonic flow around an airfoil at moderate Reynolds numbers
Direct numerical simulations of transonic flow around an airfoil at moderate Reynolds numbers
In order to reduce friction and wave drag on the wings of more efficient next generation aircraft, it is important to understand laminar-turbulent boundary-layer transition and shockwave interactions. In this contribution, fully-resolved direct numerical simulations of Dassault Aviation’s V2C profile at transonic conditions and a Reynolds number of half a million are presented. Kelvin-Helmholtz instabilities appear in the shear layers on the pressure- and
suction-sides, followed by a self-sustained laminar-turbulent transition process promoted by the stretching of rib vortices between larger co-rotating structures. Multiple acoustic structures interacting with the boundary layer are also observed, together with upstream-propagating shock waves. Regions of flow separation on the suction side exhibit unsteadiness with Strouhal numbers in the range of St 0:5 􀀀 0:6. This is distinct from a standing wave oscillation in liftat St = 0:12, which agrees well with transonic buffet frequencies, reported for experiments on the same airfoil at higher Reynolds numbers. The insensitivity of the principal results to the chosen grid resolution and spanwise domain size is carefully established.
0001-1452
Zauner, Markus
297472d4-56c0-458a-a510-ae43ecd5bd51
De Tullio, Nicola
db4397b2-3fab-476c-a0f4-4caf9848d5f7
Sandham, Neil
0024d8cd-c788-4811-a470-57934fbdcf97
Zauner, Markus
297472d4-56c0-458a-a510-ae43ecd5bd51
De Tullio, Nicola
db4397b2-3fab-476c-a0f4-4caf9848d5f7
Sandham, Neil
0024d8cd-c788-4811-a470-57934fbdcf97

Zauner, Markus, De Tullio, Nicola and Sandham, Neil (2019) Direct numerical simulations of transonic flow around an airfoil at moderate Reynolds numbers. AIAA Journal, 57 (2). (doi:10.2514/1.J057335).

Record type: Article

Abstract

In order to reduce friction and wave drag on the wings of more efficient next generation aircraft, it is important to understand laminar-turbulent boundary-layer transition and shockwave interactions. In this contribution, fully-resolved direct numerical simulations of Dassault Aviation’s V2C profile at transonic conditions and a Reynolds number of half a million are presented. Kelvin-Helmholtz instabilities appear in the shear layers on the pressure- and
suction-sides, followed by a self-sustained laminar-turbulent transition process promoted by the stretching of rib vortices between larger co-rotating structures. Multiple acoustic structures interacting with the boundary layer are also observed, together with upstream-propagating shock waves. Regions of flow separation on the suction side exhibit unsteadiness with Strouhal numbers in the range of St 0:5 􀀀 0:6. This is distinct from a standing wave oscillation in liftat St = 0:12, which agrees well with transonic buffet frequencies, reported for experiments on the same airfoil at higher Reynolds numbers. The insensitivity of the principal results to the chosen grid resolution and spanwise domain size is carefully established.

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Direct numerical simulations of transonic flow around an airfoil at moderate - Accepted Manuscript
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Accepted/In Press date: 1 November 2018
e-pub ahead of print date: 2 January 2019
Published date: February 2019

Identifiers

Local EPrints ID: 425895
URI: https://eprints.soton.ac.uk/id/eprint/425895
ISSN: 0001-1452
PURE UUID: 6c8c5bc3-40b0-435d-983b-9f27156ab570
ORCID for Markus Zauner: ORCID iD orcid.org/0000-0002-6644-2990
ORCID for Neil Sandham: ORCID iD orcid.org/0000-0002-5107-0944

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Date deposited: 06 Nov 2018 17:30
Last modified: 31 Jul 2019 00:47

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Author: Markus Zauner ORCID iD
Author: Nicola De Tullio
Author: Neil Sandham ORCID iD

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