Introduction

Davidson, Lars; Čokljat, Davor; Fröhlich, Jochen; Leschziner, M. A.; Mellen, Chris M.; Rodi, W.

doi:10.1007/978-3-540-36457-3_1

Cited by 3 publications

(3 citation statements)

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“…channel ows [30], shows a fairly strong dependency on the grid arrangement in the wall-parallel directions. In References [31,32] a hybrid LES-RANS methodology is employed in which a one-equation model is used both in the near-wall region and in the core region. The length scale in the near-wall region is related to the wall distance and the length scale is proportional to the control volume size.…”

Section: Near-wall Modellingmentioning

confidence: 99%

Hybrid LES‐RANS modelling: a one‐equation SGS model combined with a k–ω model for predicting recirculating flows

Davidson

Peng

2003

Numerical Methods in Fluids

197

105

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SUMMARYA hybrid LES-RANS modelling approach is proposed. RANS is used in the near wall regions (y + . 60), and the turbulence is modelled with a k-! model. LES is used in the remaining part of the ow, and the SGS turbulence is modelled with a one-equation ksgs model. The same continuity and momentum equations are solved throughout the domain, the only di erence being that the turbulent viscosity is taken from the k-! model in the RANS region, and from the one-equation ksgs model in the LES region. The new modelling approach is applied to two incompressible ow test cases. They are fully developed ow in a plane channel and the ow over a 2D-hill in a channel.

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Section: Near-wall Modellingmentioning

confidence: 99%

Hybrid LES‐RANS modelling: a one‐equation SGS model combined with a k–ω model for predicting recirculating flows

Davidson

Peng

2003

Numerical Methods in Fluids

197

105

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“…Under these flow conditions, the airfoil experiences a near-static stalling condition, and experiments show that flow field around airfoil is characterized by a turbulent transition through laminar separation bubble, which is then followed by turbulent reattachment and again followed by the trailing edge separation. This is considered a most difficult case to model and is used as a validation case for RANS-based models in the EUROVAL project (Haase et al , 2013) and for LES-based models in the LESFOIL project (Davidson et al , 2012).…”

Section: Results and Discussion: Standard Airfoilsmentioning

confidence: 99%

Performance of the k-kL model for aerodynamics applications

Kalkote

Kumar

Assam

et al. 2019

HFF

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Purpose The purpose of this paper is to study the predictability of the recently proposed length scale-based two-equation k-kL model for external aerodynamic flows such as those also encountered in the high-lift devices. Design/methodology/approach The two-equation k-kL model solves the transport equations of turbulent kinetic energy (TKE) and the product of TKE and the integral length scale to obtain the effect of turbulence on the mean flow field. In theory, the use of governing equation for length scale (kL) along with the TKE promises applicability in a wide range of applications in both free-shear and wall-bounded flows with eddy-resolving capability. Findings The model is implemented in the in-house unstructured grid computational fluid dynamics solver to investigate its performance for airfoils in difficult-to-predict situations, including stalling and separation. The numerical findings show the good capability of the model in handling the complex flow physics in the external aerodynamic computations. Originality/value The model performance is studied for stationary turbulent external aerodynamic flows, using five different airfoils, including two multi-element airfoils in high-lift configurations which, in the knowledge of the authors, have not been simulated with k-kL model until now.

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“…• and chord Re of 2.1 million [25]. In order to obtain good results, grids of up to 18 million points were required and even then these covered only 1:2% chord in the spanwise extent.…”

Section: Beyond Ransmentioning

confidence: 99%

The challenge of turbulence modelling in modern aeronautical design

Hutton

Ashworth

2005

Numerical Methods in Fluids

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SUMMARYModern aeronautical design is driven by a number of factors such as evolving operational requirements, the relentless drive to reduce costs and increasingly stringent environmental constraints. These have led to the requirement to treat a range of complex turbulent ow regimes. Designers demand a ÿne balance between simplicity of approach and competency, and thus research has inevitably focussed upon RANSbased turbulence modelling. This paper reviews the considerable progress of recent years in improving model proÿciency for aerodynamic applications. The limitations to what can be achieved are discussed and it is suggested that some important ow regimes are beyond the RANS approach. The opportunities for the development and adoption of more advanced strategies such as hybrid RANS=LES methods are brie y examined.

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Introduction

Cited by 3 publications

References 0 publications

Hybrid LES‐RANS modelling: a one‐equation SGS model combined with a k–ω model for predicting recirculating flows

Hybrid LES‐RANS modelling: a one‐equation SGS model combined with a k–ω model for predicting recirculating flows

Performance of the k-kL model for aerodynamics applications

The challenge of turbulence modelling in modern aeronautical design

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