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DNS of transition near the leading edge of an aerofoil

DNS of transition near the leading edge of an aerofoil
DNS of transition near the leading edge of an aerofoil
Direct numerical simulations of the three-dimensional time-dependent compressible Navier-Stokes equations are performed to investigate leading edge transition flows at realistic Reynolds number with the pressure gradient distributions from real aerofoils. The potential flow solution from an aerofoil calculation is used to setup a leading edge flowfield, which includes the stagnation point and the pressure gradient region downstream of the suction peak. A rectangular computational domain is used to retain the essential flow features with minimal computational cost. Potentially this approach could be a way to predict the lift curve of an arbitrary aerofoil.
transition, turbulence, boundary layer, adverse pressure gradient
1402001770
1382-4309
8
285-292
Springer
Alam, M.
f2a6ba6a-7dee-4083-afa8-47910bfc1b9b
Sandham, N.D.
0024d8cd-c788-4811-a470-57934fbdcf97
Geurts, Bernard J.
Friedrich, Rainer
Métais, Olivier
Alam, M.
f2a6ba6a-7dee-4083-afa8-47910bfc1b9b
Sandham, N.D.
0024d8cd-c788-4811-a470-57934fbdcf97
Geurts, Bernard J.
Friedrich, Rainer
Métais, Olivier

Alam, M. and Sandham, N.D. (2001) DNS of transition near the leading edge of an aerofoil. In, Geurts, Bernard J., Friedrich, Rainer and Métais, Olivier (eds.) Direct and Large-Eddy Simulation IV. (ERCOFTAC Series, , (doi:10.1007/978-94-017-1263-7_35), 8) Dordrecht, NL. Springer, pp. 285-292. (doi:10.1007/978-94-017-1263-7_35).

Record type: Book Section

Abstract

Direct numerical simulations of the three-dimensional time-dependent compressible Navier-Stokes equations are performed to investigate leading edge transition flows at realistic Reynolds number with the pressure gradient distributions from real aerofoils. The potential flow solution from an aerofoil calculation is used to setup a leading edge flowfield, which includes the stagnation point and the pressure gradient region downstream of the suction peak. A rectangular computational domain is used to retain the essential flow features with minimal computational cost. Potentially this approach could be a way to predict the lift curve of an arbitrary aerofoil.

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More information

Published date: 2001
Keywords: transition, turbulence, boundary layer, adverse pressure gradient
Organisations: Electronics & Computer Science

Identifiers

Local EPrints ID: 21763
URI: http://eprints.soton.ac.uk/id/eprint/21763
ISBN: 1402001770
ISSN: 1382-4309
PURE UUID: 83096b88-933a-446f-adef-bc7c43807b8e
ORCID for N.D. Sandham: ORCID iD orcid.org/0000-0002-5107-0944

Catalogue record

Date deposited: 05 Jun 2006
Last modified: 23 Jul 2020 00:27

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Contributors

Author: M. Alam
Author: N.D. Sandham ORCID iD
Editor: Bernard J. Geurts
Editor: Rainer Friedrich
Editor: Olivier Métais

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