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Large-eddy simulation of separated flow over a swept wing with approximate near-wall modelling

Published online by Cambridge University Press:  03 February 2016

N. Li  and
M. A. Leschziner
N. Li
Affiliation:
Imperial College, London, UK
M. A. Leschziner
Affiliation:
Imperial College, London, UK
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Abstract

The paper investigates, by means of a simulation methodology, the flow separating from a 40 degrees backward-swept wing at 9 degrees incidence and Reynolds number of 210,000, based on the wing-root chord length. The Simulation corresponds to LDA, PIV and suction-side-topology measurements for the same geometry, conducted by other investigators specifically to provide validation data. The finest block-structured mesh contains 23·6 million nodes and is organised in 256 blocks to maximise mesh quality and facilitate parallel solution on multi-processor machines. The near-wall layer is resolved, to a thickness of about y+ = 20, by means of parabolised URANS equations that include an algebraic eddy-viscosity model and from which the wall-shear stress is extracted to provide an unsteady boundary condition for the simulation. The numerical solution is in good agreement with the experimental behaviour over the 50-70% inboard portion of the span, but the simulation fails to resolve some complex features close to the wing tip, due to a premature leading-edge vortex breakdown and loss in vortex coherence. The comparisons and their discussion provide useful insight into various physical characteristics of this complex separated wing flow.

Type
Research Article
Information
The Aeronautical Journal , Volume 111 , Issue 1125 , November 2007 , pp. 689 - 697
Copyright
Copyright © Royal Aeronautical Society 2007 

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