By Z. J. Wang
This booklet comprises very important contributions via world-renowned specialists on adaptive high-order tools in computational fluid dynamics (CFD). It covers a number of standard, and nonetheless intensively researched tools, together with the discontinuous Galerkin, residual distribution, finite quantity, differential quadrature, spectral quantity, spectral distinction, PNPM, and correction process through reconstruction equipment. the focus is purposes in aerospace engineering, however the ebook must also be priceless in lots of different engineering disciplines together with mechanical, chemical and electric engineering. when you consider that lots of those tools are nonetheless evolving, the publication can be an outstanding reference for researchers and graduate scholars to realize an figuring out of the state-of-the-art and final demanding situations in high-order CFD equipment.
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Extra resources for Adaptive High-Order Methods in Computational Fluid Dynamics
The parameters of the restarted GMRES solver have been set to 60 Krylov subspace vectors and 120 maximum iterations for the coarse grid solutions, and to 120 vectors and 480 iterations for the fine grid solutions. Figure 16 shows the residuals convergence history of the coarse-grid solutions in terms of Newton iterations and performance index units. The coarse and fine grid computations have been run in parallel using respectively 128 and 512 cores December 1, 2010 16:28 World Scientific Review Volume - 9in x 6in 25 DG for Turbulent Flows Table 4.
Table 3. ONERA M6: lift and drag coefficients of DG solutions. 8. Despite the quite coarse grid resolution, the P2 solution is also capable of capturing the flow separation near the wing tip, as shown in Figure 9. Table 3 reports the force coefficients of P0→2 solutions, showing that at least a one-degree higher P3 solution would be useful to assess the convergence of force coefficients. January 17, 2011 12:9 World Scientific Review Volume - 9in x 6in 22 F. Bassi et al. Fig. 9. ONERA M6: flow separation near the wing tip of P2 solution.
Figure 15 highlights the capability of the P3 solution to capture the detail of flow separation at the wing-root junction on the given coarse-grid. Table 4 reports the force and pitching moment coefficients computed on the coarse and fine grids. There is a discrepancy between the more accurate results on the two grids that needs to be further investigated and no clear conclusion can be drawn about the asymptotic values of the aerodynamic coefficients. One issue could be the poor geometrical approximation of surfaces when using only quadratic mappings for the faces of very coarse meshes.