Titlebook: Sixteenth International Conference on Numerical Methods in Fluid Dynamics; Proceedings of the C Charles-Henri Bruneau Conference proceeding

口味

Efficient calculation of 3-D turbulent transonic flows, technique. The scheme is driven to steady-state by various implicit treatments, the pros and cons of which are discussed in terms of cost and memory requirement. The efficiency and accuracy of the proposed methods are assessed by computing transonic flows over wings.

SEVER

乏味

Time-accurate fluid-structure coupling for turbulent flows,ulent transonic flows around airfoils in arbitrary motion. The resolution of the structural system resolution is performed with an unconditionnally stable algorithm. Computations of two test cases with forced oscillation and one with flutter are analyzed.

充氣女

Distribution

Hybrid-cartesian grid procedure for the simulation of compressible turbulent flows,h made of general polygonal elements is obtained by intersecting hyperbolic grids generated in the boundary layers and in the wakes with a Cartesian grid covering the whole domain of computation. The flow solver is based on a cell-centered high-order finite volume scheme. A multigrid preconditioned

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Nibble

Numerical simulations of two blasts by a supersonic projectile discharged from a tube,ube into ambient air. The Euler equations, assuming axisymmetric flows, were solved using a dispersion-controlled scheme implemented with moving boundary conditions. The numerical results show that not only does the leading shock due to the second blast overtake the projectile but also the gas behin

Myocyte

Numerical study of effects of a bellmouth on the entrance pipe flow, Until now, the axial velocity has been assumed to be uniform at the bellmouth outlet. The calculation results, however, reveal that it develops a profile somewhat towards the Poiseuille’s parabolic profile. Moreover, a feasible reason for the increase in critical Reynolds number when using bellmout

調(diào)色板

A fast, matrix-free implicit method for compressible flows on unstructured grids,e system of linear equations arising from the Newton linearization is solved by the GMRES (Generalized Minimum RESidual) algorithm with a LU-SGS (Lower-Upper Symmetric Gauss-Seidel) preconditioner. A remarkable feature of the present GMRES+LU-SGS method is that the storage of the Jacobian matrix can

長(zhǎng)矛

A supersonic inverse wing design method and its application to Japanese SST,r has been devised. The method handles SST wing-fuselage configurations and provides the wing section geometry at every span station. It uses the inverse problem solver and Navier-Stokes simulation. The design target is a natural laminar flow (NLF) wing for the wing-fuselage combination at the speed