Modelling of turbulent transonic flow around aerofoils and wings

Müller, Bernhard; Rizzi, Arthur

doi:10.1002/cnm.1630060805

Cited by 6 publications

(3 citation statements)

References 9 publications

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“…5 use the wall enhancement k−ε turbulence mode. The numerical solution at the sublayer region is presented at y + < 10 which agrees very well with log law, the latter being computed from the equation U + = 2.44 ln( y + ) + 5.55 (6) The BL mesh near the wall must be sufficiently refined to increase the accuracy of the results at this area. Beyond y + = 10 the flow structure appears to deviate from the log law.…”

Section: Fully Developed Channel Flowmentioning

confidence: 75%

“…Channel flow constitutes a fundamental problem arising in many engineering systems. Müller and Rizzi [6] compute turbulent transonic flow over the NACA 0012 aerofoil and also the ONERA M6 wing by solving the 2D and 3D Navier-Stokes equations in quadrilaterals and hexahedrons, respectively, employing an algebraic eddy viscosity model and the finite-volume method. heat transfer, species transfer, etc).…”

Section: Introductionmentioning

confidence: 99%

“…In this study, the authors also consider the simulation of turbulent boundary layer (BL) flow on a NACA 0012 aerofoil, one of the most intensively examined blade geometries. Müller and Rizzi [6] compute turbulent transonic flow over the NACA 0012 aerofoil and also the ONERA M6 wing by solving the 2D and 3D Navier-Stokes equations in quadrilaterals and hexahedrons, respectively, employing an algebraic eddy viscosity model and the finite-volume method. Tenaud and Phuoc [7] utilized a mixed-scale subgrid model for compressible flow simulation of a NACA 0012 aerofoil at free stream Mach number at high Reynolds number 200 000.…”

Section: Introductionmentioning

confidence: 99%

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Numerical investigations of wall-bounded turbulence

Daud

Bég

et al. 2011

Proceedings of the Institution of Mechanical Engineers, Part C:

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This article investigates numerically the effects on turbulence in two important flow regimes -fully developed channel flow and flow past a NACA 0012 airfoil, using the commercial software -FLUENT 6.3. The solution accuracy is explored via a sensitivity study of mesh type and quality effects, employing different element types (e.g. quadrilateral and triangular). The significance of this article is to elucidate the effects of enhancement wall treatment and standard wall function on the turbulent boundary layer. Furthermore, three different turbulence models have been utilized in this study (k−ε, re-normalization group (RNG), and shear stress transport (SST) k−ω). The numerical solutions have been compared with available direct numerical simulation (DNS) and experimental data and very good correlation has been achieved. In addition, the statistical turbulence results related to the RNG turbulence model are shown to yield much closer correlation with DNS and experimental data. The effect of Reynolds number (Re τ = 590 and Re τ = 2320) is studied for the channel flow regime. The near wall resolution is examined in detail by controlling in the y + value. A particularly important objective in this study is to highlight the importance of validation in computational fluid dynamics (CFD) turbulence simulations and sustaining a high degree of accuracy, aspects which are often grossly neglected with industrial CFD software. The authors therefore hope to provide some guidance to applied aerodynamicists utilizing CFD in future studies.

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Section: Fully Developed Channel Flowmentioning

confidence: 75%

Section: Introductionmentioning

confidence: 99%