Download Sixteenth International Conference on Numerical Methods in by Marsha Berger, Michael Aftosmis (auth.), Charles-Henri PDF

By Marsha Berger, Michael Aftosmis (auth.), Charles-Henri Bruneau (eds.)

This booklet covers a large quarter of issues, from primary theories to business purposes. It serves as an invaluable reference for all drawn to computational modeling of partial differential equations pertinent basically to aeronautical functions. The reader will locate 5 survey articles on cartesian mesh tools, on numerical stories of turbulent boundary layers, on effective computation of compressible flows, at the use of Riemann-solvers and on numerical systems in advanced flows.

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Read Online or Download Sixteenth International Conference on Numerical Methods in Fluid Dynamics: Proceedings of the Conference Held in Arcachon, France, 6 – 10 July 1998 PDF

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Additional info for Sixteenth International Conference on Numerical Methods in Fluid Dynamics: Proceedings of the Conference Held in Arcachon, France, 6 – 10 July 1998

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3 Implicit time integration The calculation of steady-state flows is performed by using Newton's method. In order to improve the nonlinear convergence, a mesh sequencing and a pseudo-transient continuation [Kelley and Keyes (98)] technique are used. The latter technique solves the stationary Favre-averaged Navier-Stokes equations through a pseudo-time integration with a variable timestep which is increased inversely to the residual norm. At each timestep a finite difference version of the GMRES algorithm [Brown and Saad (90)] solves the linear system arising from the Newton linearization using an inexact Newton convergence criterion.

Thus, the ALE approach is achieved by computing absolute fluxes and translating the eigenvalues of A. A U S M + s c h e m e on d y n a m i c meshes. The basic idea of the A U S M splitting of [Liou & Stephen (93)] is to recognize convection and acoustic waves propagation as two distinct processes and to treat them separately Hin=Hcn+Hpn, where Hcn=Mra~ and Hvn=pH the speed of sound a = ~ , the relative Mach number Mr : ( V - ~ ) n / a , = [p, pV, ph]t where h is the enthalpy and H = [0, n, ~n] t.

Rapid Convergence of Airfoil Design Problems Using Progressive Optimization A. Dadone and B. Grossman Istituto Macchine, Politecnico di Bari, Via Re David 200, 70125 Bari, ITALY Virginia Tech, Dept. , Blacksburg, VA 24061, USA email: dadone @irnedado. poliba, it,grossman@aoe, vt. edu K e y W o r d s : AIRFOIL, INVERSE DESIGN, DIRECT DESIGN, EULER FLOW A b s t r a c t . An efficient formulation for the robust design optimization of compressible fluid flow problems is presented. The methodology has three essential ingredients: a highly accurate flow solver, robust and efficient design sensitivities from a discrete adjoint formulation based on a dissipative flow solver and progressive optimization, whereby a sequence of operations, containing a partially converged flow solution, followed by an adjoint solution followed by an optimization step is performed.

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