Finite differences for coarse azimuthal discretization and for reduction of effective resolution near origin of cylindrical flow equations

Bogey, Christophe; Cacqueray, Nicolas de; Bailly, Christophe

doi:10.1016/j.jcp.2010.10.031

Cited by 84 publications

(65 citation statements)

References 34 publications

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“…For the treatment of the axis singularity, the method proposed by Mohseni and Colonius [48] is used, and to increase the time step the effective azimuthal resolution is reduced near the jet centerline [49]. The LES approach is based on the explicit application of a relaxation filtering to the flow variables [50] to take into account the dissipative effects of the subgrid scales.…”

Section: B Numerical Methodsmentioning

confidence: 99%

Investigation of a High-Mach-Number Overexpanded Jet Using Large-Eddy Simulation

2011

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An initially laminar overexpanded round jet at an exit Mach number of 3.30 and a Reynolds number of 10 5 is calculated by compressible large-eddy simulation. The near field obtained by large-eddy simulation is also propagated to the acoustic far field by solving the full Euler equations to take into account the nonlinear propagation effects. Both computations are performed using low-dissipation finite differences in combination with an adaptive shock-capturing method. The jet originates from a straight pipe nozzle of radius r e , including lips of thickness 0:05r e . At the pipe exit, Blasius mean flow profiles are imposed, and static pressure and temperature are equal to 0:5 10 5 Pa and 360 K, resulting in fully adapted and acoustic Mach numbers, respectively, of 2.83 and 3.47. The jet flowfields, as well as the acoustic near and far fields, are described in detail and compared with data of the literature. The turbulent mechanisms developing in the jet are investigated, using spectral and azimuthal decompositions of the velocity fluctuations along the shear layers. Same analyses are applied to the acoustic fields, in order to discuss the properties of jet noise components. In this way, Mach waves, shock-associated noise, screech tones, and turbulent mixing noise are identified. = first shock location on the jet axis = specific heat ratio r = mesh size in the radial direction z = mesh size in the axial direction = boundary-layer thickness in the pipe nozzle 0:5 = jet half-width e = exit molecular viscosity e = exit density = radiation angle measured according to the flow direction

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Section: B Numerical Methodsmentioning

confidence: 99%

Investigation of a High-Mach-Number Overexpanded Jet Using Large-Eddy Simulation

2011

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“…The axis singularity is treated with the method proposed by Mohseni and Colonius [25]. A reduction of the effective resolution near the origin of the polar coordinates is also implemented [26]. Finally, a forcing [27] is added in the boundary layer in the nozzle to generate velocity fluctuations at the nozzle exit.…”

Section: B Numerical Parametersmentioning

confidence: 99%

Flow Features near Plate Impinged by Ideally Expanded and Underexpanded Round Jets

Gojon

Bogey

2018

AIAA Journal

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“…Figure 3 illustrates the finite difference computation in [3], which is based on a cylindrical coordinate grid. The grid gets coarser near do k = 1, n3 do j = 1, n2 call thomas(n1, dl ,d,du,x(: , j ,k)) end do end do end subroutine the origin in order to avoid the exceedingly fine resolution that can impose a severe restriction on the advance of the time steps.…”

Section: The Stride Transformationmentioning

confidence: 99%

“…The multi-grid method can be expressed by setting the grids_list to be a single scalar. The method used in [3] is a special case, in which several coarser grids are formed and all must be solved. This case can be expressed by setting grids_list to be 1 : s : 1.…”

Section: The Stride Transformationmentioning

confidence: 99%

“…It is well-known that the decrease in azimuthal spacing in the vicinity of the centerline increases the computational cost. One solution proposed by Bogey et al [3] for this problem is to use coarser grids in the vicinity of the centerline. For a coarsening level of n, 2 n−1 number of rings are coarsen by a factor of 2 i (i is from 1 to n) in forming the tridiagonal and derivative systems.…”

Section: Centerline Treatment For a Cylindrical Gridmentioning

confidence: 99%

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GridFOR: A Domain Specific Language for Parallel Grid-Based Applications

Wang

2015

Int J Parallel Prog

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To ease the programming burden and to make parallel programs more maintainable, computational scientists and engineers currently have the options to use software libraries, templates, and general purpose language extensions to compose their application programs. These existing options, unfortunately, have considerable limitations with compatibility, expressive power and delivered performance. To address these issues, we design a domain specific language, GridFOR, for computational problems defined over regular geometric grids. This language allows the programmer to first implement an algorithm on simple data structures, as commonly illustrated in textbooks or papers. The programmer then specifies transformations to extend the algorithm for complex data structures required by the target applications. We build a compiler to automatically translate a GridFOR program to a parallel Fortran version with Message Passing Interface calls. Several optimization techniques are implemented in our compiler to enhance the program speed.

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Finite differences for coarse azimuthal discretization and for reduction of effective resolution near origin of cylindrical flow equations

Cited by 84 publications

References 34 publications

Investigation of a High-Mach-Number Overexpanded Jet Using Large-Eddy Simulation

Investigation of a High-Mach-Number Overexpanded Jet Using Large-Eddy Simulation

Flow Features near Plate Impinged by Ideally Expanded and Underexpanded Round Jets

GridFOR: A Domain Specific Language for Parallel Grid-Based Applications

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