Automated Hybrid Mesh Generation for Industrial High-Lift Applications

Munday, S; Martineau, David; Gribben, B.; Verhoeven, N.A.

doi:10.2514/6.2007-268

Cited by 9 publications

(3 citation statements)

References 7 publications

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“…(12) for wall boundaries). Similarly, the vector-valued numerical flux functionû h in (8) is an approximation to u h and is given byû h =û(u h ) =û(u + h , u − h ) on interior faces and byû h | Γ =û Γ,h =û Γ (u + h ) on boundary faces.…”

Section: Discontinuous Galerkin Discretization Of the Governing Fmentioning

confidence: 99%

High-order unstructured grid generation and Discontinuous Galerkin discretization applied to a 3D high-lift configuration

Hartmann

Leicht

2015

53rd AIAA Aerospace Sciences Meeting

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Discontinuous Galerkin (DG) methods allow high-order flow solutions on unstructured or locally refined meshes by increasing the polynomial degree and using curved instead of straight-sided elements. However, one of the currently largest obstacles to applying these methods to aerodynamic configurations of medium to high complexity is the availability of appropriate higher order curved meshes.In this article, we describe a complete chain of higher order unstructured grid generation and higher order Discontinuous Galerkin flow solution applied to a turbulent flow around a 3D high-lift configuration. This includes (i) the generation of an appropriately coarse straight-sided mesh, (ii) the evaluation of additional points on the CAD geometry of the curved wall boundary for defining a piecewise polynomial boundary representation, (iii) a higher order mesh deformation to translate the curvature from the wall boundary into the interior of the computational domain, and (iv) the description of a Discontinuous Galerkin discretization which is sufficiently stable to allow a flow computation on the resulting curved mesh. Finally, a fourth order flow solution of the RANS and k-ω turbulence model equations is computed on a fourth order unstructured hybrid mesh around the 3D high-lift SWING configuration.

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Section: Discontinuous Galerkin Discretization Of the Governing Fmentioning

confidence: 99%

High-order unstructured grid generation and Discontinuous Galerkin discretization applied to a 3D high-lift configuration

Hartmann

Leicht

2015

53rd AIAA Aerospace Sciences Meeting

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“…In addition to the baseline CENTAUR grids partners from the Center of Computer Applications in Aerospace Science and Engineering (C²A²S²E) have generated a grid with the mesh generator tools of the SOLAR CFD 11 system. Its quadrilateral dominant surface grids and the corresponding hexahedral dominant layers near the surfaces offer a high potential for high lift applications by aligning the surface and volume elements with the main direction of the flow.…”

Section: Solar Gridsmentioning

confidence: 99%

Numerical Maximum Lift Predictions of a Realistic Commercial Aircraft in Landing Configuration

Bier

Rohlmann

Rudnik

2012

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Within task three "Numerical Simulations" in the project "HINVA-High Lift INflight Validation" extensive numerical verification studies based on a CAD model of DLR's A320-232 "Advanced Technology Research Aircraft" in landing configuration are carried out. Therein special attention is paid to the effect of certain geometric features of the high-lift system, such as slat tracks, de-icing pipe etc. Also the empennage and a model of both the operational engine and a through flow nacelle are included in the geometry. The numerical simulations are carried out using two different sets of flow solver settings. The first based on the Spallart-Allmaras turbulence model represents DLR's current best-practice. The second set follows a high-precision approach based on a differential Reynolds stress turbulence model. In this paper the structure of the task is presented along with results of initial numerical simulations assessing the influence of the slat tracks, the de-icing pipe and the TFN in comparison to the operational engine.

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“…There has been dedicated effort on the development of unstructured higher‐order grid generation for aerodynamic applications in the European projects ADIGMA and IDIHOM . For example, ARA worked on extending the SOLAR mesh generator to the generation of quadratic meshes. Their development based on the assumption that a quadratic treatment in the prismatic boundary layer mesh is sufficient, while the tetrahedra in the farfield mesh can stay linear .…”

Section: Introductionmentioning

confidence: 99%

Generation of unstructured curvilinear grids and high‐order discontinuous Galerkin discretization applied to a 3D high‐lift configuration

Hartmann

Leicht

2016

Numerical Methods in Fluids

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SUMMARYDiscontinuous Galerkin (DG) methods allow high-order flow solutions on unstructured or locally refined meshes by increasing the polynomial degree and using curved instead of straight-sided elements. However, one of the currently largest obstacles to applying these methods to aerodynamic configurations of medium to high complexity is the availability of appropriate higher-order curved meshes.In this article, we describe a complete chain of higher-order unstructured grid generation and higherorder DG flow solution applied to a turbulent flow around a three-dimensional high-lift configuration. This includes (i) the generation of an appropriately coarse straight-sided mesh; (ii) the evaluation of additional points on the computer-aided design geometry of the curved-wall boundary for defining a piecewise polynomial boundary representation; (iii) a higher order mesh deformation to translate the curvature from the wall boundary into the interior of the computational domain; and (iv) the description of a DG discretization, which is sufficiently stable to allow a flow computation on the resulting curved mesh. Finally, a fourth-order flow solution of the Reynolds-averaged Navier-Stokes and k-! turbulence model equations is computed on a fourth-order unstructured hybrid mesh around the three-dimensional high-lift simulation of wing-flow noise generation configuration.

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Automated Hybrid Mesh Generation for Industrial High-Lift Applications

Cited by 9 publications

References 7 publications

High-order unstructured grid generation and Discontinuous Galerkin discretization applied to a 3D high-lift configuration

High-order unstructured grid generation and Discontinuous Galerkin discretization applied to a 3D high-lift configuration

Numerical Maximum Lift Predictions of a Realistic Commercial Aircraft in Landing Configuration

Generation of unstructured curvilinear grids and high‐order discontinuous Galerkin discretization applied to a 3D high‐lift configuration

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