Accurate Computation of 2D Turbulent Compressible Flows on Unstructured Grids

Catalano, L. A.; Daloiso, V. S. E.

doi:10.2514/6.2003-3828

Cited by 3 publications

(7 citation statements)

References 9 publications

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“…Figures 3 and 4 provide the Mach number contours ( M = 0:05) for the channel ow and for the inviscid transonic ow past the airfoil, respectively. Very ÿne grids (about 14 000 cells) have been employed in all applications to better test both the LS and the IRS strategies, the accuracy of the space discretization already having been demonstrated in References [1][2][3].…”

Section: Resultsmentioning

confidence: 99%

“…All gradients must be computed once at each iteration, stored, and then used without any additional averaging. For this reason, and since the same gradients must be computed anyway when solving the Navier-Stokes equations, the authors claim that the proposed higher-order reconstruction minimizes the computational time required for the evaluation of the ow gradients [1][2][3].…”

Section: Space Discretizationmentioning

confidence: 99%

“…Most methods for unstructured grids proposed to date employ a cell-vertex discretization, since it allows a natural deÿnition of the cellbased ow gradients, which are required both for the higher-order reconstruction and for the discretization of the viscous terms. In the framework of a ÿnite-volume approach, the authors have recently developed and validated a new higher-order accurate 2D and 3D gradient-based reconstruction to discretize the convective terms of the Navier-Stokes equations [1][2][3]. The reconstruction employs the same (cell-based) gradients needed for the discretization of the di usive terms, with no additional averaging.…”

Section: Introductionmentioning

confidence: 99%

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Upwinding and implicit residual smoothing on cell‐vertex unstructured grids

Catalano

Daloiso

2005

Numerical Methods in Fluids

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SUMMARYA new line-search algorithm for cell-vertex unstructured triangular grids is proposed in this paper and combined with an implicit residual smoothing procedure, to accelerate convergence of a recently developed upwind ÿnite-volume method for the Euler and the Navier-Stokes equations. Both the standard implementation with two smoothing lines and a new procedure using four directions are considered and fully tested to evaluate their e ciency and to determine the optimal smoothing parameters.

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Section: Resultsmentioning

confidence: 99%

Section: Space Discretizationmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Upwinding and implicit residual smoothing on cell‐vertex unstructured grids

Catalano

Daloiso

2005

Numerical Methods in Fluids

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“…The flux-difference-splitting of (Roe, 1986) is then used to solve the Riemann problem defined at each interface. It is noteworthy that this rather simple method allows to capture discontinuities very sharply, despite the 1-D physics of the Riemann solver (Catalano et al, 2003b). Figure 2 provides the Mach number contours for the flow in a circular-arc bump channel, with M inl = 1.4, computed on a grid composed by 15 256 cells.…”

Section: Second-order Reconstructionmentioning

confidence: 99%

Turbine cascade design via multigrid-aided finite-difference progressive optimization

Catalano¹,

Dadone²,

Daloiso³

2008

TECM

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This paper proposes an efficient and robust procedure for the design optimization of turbomachinery cascades in inviscid and turbulent transonic flow conditions. It employs a progressive strategy, based on the simultaneous convergence of the design process and of all iterative solutions involved (flow analysis, gradient evaluation), also including the global refinement from a coarse to a sufficiently fine mesh. Cheap, flexible and easy-to-program Multigrid-Aided Finite Differences are employed for the computation of the sensitivity derivatives. The entire approach is combined with an upwind finite-volume method for the Euler and the Navier-Stokes equations on cell-vertex unstructured (triangular) grids, and validated versus the inverse design of a turbine cascade. The methodology turns out to be robust and highly efficient, the converged design optimization being obtained in a computational time equal to that required by 15 to 20 (depending on the application) multigrid flow analyses on the finest grid.

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“…The upwind second-order-accurate flow solver for unstructured grids described in References [11,12] is used to compute the flow field.…”

Section: Multigrid-aided Finite-difference Progressive Optimizationmentioning

confidence: 99%

On the use of orthogonal functions in fluid‐dynamic gradient‐based optimization

Catalano

Dadone

Daloiso

2008

Numerical Methods in Fluids

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SUMMARYThis paper proposes a method to derive a set of symmetrical and antisymmetric orthogonal shape functions, which can be efficiently used in fluid-dynamic design optimization. The inverse design of an airfoil in inviscid transonic flow conditions is proposed to demonstrate that a gradient-based optimization using orthogonal profiles is 6-10 times faster than the same procedure using non-orthogonal interpolation functions.

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Accurate Computation of 2D Turbulent Compressible Flows on Unstructured Grids

Cited by 3 publications

References 9 publications

Upwinding and implicit residual smoothing on cell‐vertex unstructured grids

Upwinding and implicit residual smoothing on cell‐vertex unstructured grids

Turbine cascade design via multigrid-aided finite-difference progressive optimization

On the use of orthogonal functions in fluid‐dynamic gradient‐based optimization

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