One-Equation RG Hybrid RANS/LES Modelling

Langhe, Chris De; Bigda, J.; Lodefier, Koen; Dick, Erik

doi:10.1007/978-3-540-77815-8_10

Cited by 11 publications

(3 citation statements)

References 13 publications

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“…A one-equation Renormalization Group (RG) model proposed by De Langhe et al 15,16 was employed for the hybrid simulations. Hybrid turbulence models blend between Large Eddy Simulation (LES) and ReynoldsAveraged Navier-Stokes (RANS) depending on the local physical grid resolution.…”

Section: A Governing Equationsmentioning

confidence: 99%

Numerical Investigation of Separation Control for Wing Section at Re=300,000

Groß

Fasel

2013

43rd Fluid Dynamics Conference

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Active flow control by harmonic blowing through a slot is investigated for a modified NACA643-618 airfoil at a chord Reynolds number of Re=300,000 and for 15 degrees angle of attack. A direct simulation of the uncontrolled flow serves as a reference for hybrid simulations using a one-equation renormalization group turbulence model. Because of their lower computational expense, two-dimensional hybrid calculations are employed for active flow control parameter studies. Downstream harmonic blowing through a spanwise slot is investigated. For a blowing ratio of 0.1 the control is ineffective. For blowing ratios and dimensionless forcing frequencies between one and two the actuation results in vortex shedding of the separated boundary layer and a moderate rise in lift.

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Section: A Governing Equationsmentioning

confidence: 99%

Numerical Investigation of Separation Control for Wing Section at Re=300,000

Groß

Fasel

2013

43rd Fluid Dynamics Conference

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“…The resulting increased wall-normal mixing leads to a transport of high-momentum freestream fluid towards the wall, thus reducing the extent of the separation or even completely eliminating it. [1,2,4] For α = 10 active flow control by harmonic blowing, (13) through a spanwise slot with amplitude, A, was investigated. Two pitch angles, ϕ = 30 deg and 90 deg (wall normal blowing), were considered.…”

Section: Controlled Flowmentioning

confidence: 99%

“…Away from walls, depending on the local physical grid resolution, the model reverts to LES or DNS. For the hybrid simulations presented in this paper, a one-equation Renormalization Group (RG) model proposed by De Langhe et al [13,14] was employed.…”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation of Separation Control for Wing Sections

Groß

Fasel²

2013

International Journal of Flow Control

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For Reynolds numbers that are typical for general aviation aircraft separation is typically turbulent. In this paper the question is addressed if flow control strategies that are successful at low-Reynolds number conditions remain effective at higher Reynolds numbers. Towards this end hybrid simulations based on a one-equation renormalization group model were carried out for a modified NACA643-618 airfoil at a chord Reynolds number of one million. For ten degrees angle of attack a short laminar separation bubble develops near the leading edge and the flow separates turbulent from the suction side downstream of the leading edge bubble. Active flow control by harmonic blowing through a spanwise slot was investigated. The control was found to be only mildly effective or even counterproductive. In particular, the disturbances that were introduced by the control were only weakly amplified or even dampened. The unresolved eddy viscosity in the separated boundary layer lowers the effective Reynolds number and makes the flow less unstable or even stable with respect to two-dimensional disturbances. As a consequence of this, higher blowing ratios are required compared to flow control at low-Reynolds number conditions where the shear-layer instability is stronger. *

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Hybrid Turbulence Model Simulations of Partially Stalled Airfoil Flow

Groß

Fasel

2016

AIAA Journal

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One-Equation RG Hybrid RANS/LES Modelling

Cited by 11 publications

References 13 publications

Numerical Investigation of Separation Control for Wing Section at Re=300,000

Numerical Investigation of Separation Control for Wing Section at Re=300,000

Numerical Investigation of Separation Control for Wing Sections

Hybrid Turbulence Model Simulations of Partially Stalled Airfoil Flow

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