Finite Element Flow Simulations of the EUROLIFT DLR-F11 High Lift Configuration

Abstract

This paper presents flow simulation results of the EUROLIFT DLR-F11 multi-element wing configuration, obtained with a highly scalable finite element solver, PHASTA. This work was accomplished as a part of the 2 nd high lift prediction workshop. In-house meshes were constructed with increasing mesh density for analysis. A solution adaptive approach was used as an alternative and its effectiveness was studied by comparing its results with the ones obtained with other meshes. Comparisons between the numerical solution obtained with unsteady RANS turbulence model and available experimental results are provided for verification and discussion. Based on the observations, future direction for adaptive research and simulations with higher fidelity turbulence models is outlined.

Anisotropic Boundary Layer Adaptivity of Multi-Element Wings

“…As a part of the 2 nd high-lift prediction workshop, coarse, medium and fine meshes were constructed for this geometry. Comparison of adapted mesh results with these progressively refined meshes is given in more details in Chitale et al 23 Table 4 shows comparison of C L and C D for the initial and the adapted meshes with experimental values. Clearly, the adapted mesh results are closer to the experiments than the initial mesh, especially C L .…”

Grid-Adapted FUN3D Computations for the Second High-Lift Prediction Workshop

“…An overview and summary of the workshop is given by Rumsey and Slotnick [2]. Many workshop participants have summarized individual submissions and provided additional analysis and computations [3][4][5][6][7][8][9][10][11].…”

On the simulation of steady and unsteady incompressible flows using the finite volume approach and artificial compressibility concept on hybrid unstructured girds

“…Due to the size of the provided meshes and restrictions in computational resources, simulation was carried out on the more simple geometry; Config 2 was selected, where the wing consisted of the three components, without the support brackets, or the pressure tube bundles. Although as it was demonstrated by Chitale et al [Chi14], these brackets alter the flow behavior, especially under the wing, simulation of the flow around the simpler configuration provided adequate results, capable of demonstrating the current code's capabilities. The simulation was performed for angles of attack equal to 7 o and 12 o .…”

“…In Figure 5.92 the vorticity contours at the wake of the DLR-F11 wing were sketched on successive X-Y parallel planes, in order to picture the wingtip vortex that is generated in that area. The computed results are compared qualitatively to those from Chitale et al [Chi14], who published similar illustrations of the vorticity contours at the same region. As it can be observed, the vorticity contours predicted with the Galatea-I software are of slightly better quality than the ones produced with the Medium mesh (approx.…”