High Lift CFD Simulations with an SST-Based Predictive Laminar to Turbulent Transition Model

Steed, Robin

doi:10.2514/6.2011-864

Cited by 12 publications

(8 citation statements)

References 3 publications

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“…[5][6][7][8][9][10][11][12][13][14][15][16][17][18] Most of these studies involved a few wellknown "standard" turbulence models such as Spalart-Allmaras (SA) 19 and Menter's shear-stress transport (SST) 20 applied in fully turbulent mode. At the workshop, SA (fully turbulent) was heavily favored because it tended to yield closer agreement to experiment for the Trapezoidal Wing.…”

Section: Introductionmentioning

confidence: 99%

NASA Trapezoidal Wing Computations Including Transition and Advanced Turbulence Modeling

Rumsey

Lee-Rausch

2015

Journal of Aircraft

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Flow about the NASA Trapezoidal Wing is computed with several turbulence models by using grids from the first High Lift Prediction Workshop in an effort to advance understanding of computational fluid dynamics modeling for this type of flowfield. Transition is accounted for in many of the computations. In particular, a recently-developed 4-equation transition model is utilized and works well overall. Accounting for transition tends to increase lift and decrease moment, which improves the agreement with experiment. Upper surface flap separation is reduced, and agreement with experimental surface pressures and velocity profiles is improved. The predicted shape of wakes from upstream elements is strongly influenced by grid resolution in regions above the main and flap elements. Turbulence model enhancements to account for rotation and curvature have the general effect of increasing lift and improving the resolution of the wing tip vortex as it convects downstream. However, none of the models improve the prediction of surface pressures near the wing tip, where more grid resolution is needed.

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Section: Introductionmentioning

confidence: 99%

NASA Trapezoidal Wing Computations Including Transition and Advanced Turbulence Modeling

Rumsey

Lee-Rausch

2015

Journal of Aircraft

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“…However, it was noted that transition could play a significant role for this case (Reynolds number based on mean aerodynamic chord was 4.3 million). Several participants [31][32][33] subsequently demonstrated that a transition-enabled version of the SST model (γ-Re θ SST) 34 performed much better than SST run fully turbulent. Eliasson et al 35 demonstrated similar improvements for the SA model using an e N transition method.…”

Section: Dpw and Hiliftpw Seriesmentioning

confidence: 99%

Turbulence Modeling Verification and Validation (Invited)

Rumsey

2014

52nd Aerospace Sciences Meeting

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Turbulence modeling for the Reynolds-averaged Navier-Stokes (RANS) equations includes many assumptions and simplifying closures. Numerous models have been developed over the years, and all are deficient in one way or another. Many collective efforts have attempted to validate turbulence models for a wide range of problems, but conclusions have often been muddied due to the lack of grid convergence, lack of model verification in different codes, or for other reasons. In this paper, turbulence modeling verification and validation is discussed primarily within the context of several recent workshops. A web-based turbulence modeling resource is also described, whose goals include turbulence model documentation, verification, and validation. Using this resource, specific models can easily be put through a verification testing procedure, helping to eliminate coding errors.

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“…Steed (Steed, 2011) used a NASA Trapezoidal Wing model in his study. The researcher used SST based laminar to transition model and compared the results with both fully turbulent SST and wind tunnel results.…”

Section: Introductionmentioning

confidence: 99%

Başlangıç y plus Değerinin Etkileri: γ-Reθ SST Türbülans Modeli Kullanılarak 3D NACA 4412 Kanadının Sayısal Analizi

Körpe¹,

Kanat²,

Oktay³

2019

European Journal of Science and Technology

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In this numerical study, the effects of the initial y plus, which is a dimensionless wall distance, on the results of aerodynamic coefficients of designed a wing using NACA 4412 airfoil are investigated. For this purpose, the wing is designed and external flow analysis is carried out according to constant altitude. ANSYS Fluent, which is a Computational Fluid Dynamics (i.e. CFD) program and solves the problems according to the Finite Volume Method (i.e. FVM), is used for external flow analysis. Pressure-based method is used for numerical studies. Thus, the differences of coefficients on the wall, which are the results of the change in the initial y plus, are calculated ideally. Because of one of the best methods to solve the problems on transition zone, γ-Reθ SST turbulence model is used for this study. Using this model for each analysis, first element heights (i.e. the distance to the nearest wall) are calculated according to 9 different y plus (i.e. 1, 5, 10, 30, 45, 60, 75, 90, 105). According to the first element heights, the inflation layers are created on the wing and the 3D control volumes are formed along the boundary region. To be more comprehensible, orthogonal quality-skewness values, expressing the quality of control volumes, are presented for each boundary. The changes in lift coefficients and drag coefficients on the same wing according to these 9 different y plus are presented numerically. In addition, obtained results are evaluated and as described in the literature, it is observed that to calculate the aerodynamic forces with the γ-Reθ SST turbulence model is directly proportional to the initial y plus. As a consequence, this paper demonstrates that there are obvious differences detection of separation and determination of reattach region of flow occurring on the wing according to the initial y plus.

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High Lift CFD Simulations with an SST-Based Predictive Laminar to Turbulent Transition Model

Cited by 12 publications

References 3 publications

NASA Trapezoidal Wing Computations Including Transition and Advanced Turbulence Modeling

NASA Trapezoidal Wing Computations Including Transition and Advanced Turbulence Modeling

Turbulence Modeling Verification and Validation (Invited)

Başlangıç y plus Değerinin Etkileri: γ-Reθ SST Türbülans Modeli Kullanılarak 3D NACA 4412 Kanadının Sayısal Analizi

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