Turkel, E.
Overview
Works:  102 works in 255 publications in 1 language and 4,196 library holdings 

Roles:  Author, Editor 
Publication Timeline
.
Most widely held works by
E Turkel
Accuracy of schemes with nonuniform meshes for compressible fluid flows by
E Turkel(
)
4 editions published in 1985 in English and held by 298 WorldCat member libraries worldwide
4 editions published in 1985 in English and held by 298 WorldCat member libraries worldwide
Accuracy of schemes for the Euler equations with nonuniform meshes by
E Turkel(
)
5 editions published in 1985 in English and held by 297 WorldCat member libraries worldwide
5 editions published in 1985 in English and held by 297 WorldCat member libraries worldwide
Application of a RungeKutta scheme for highspeed inviscid internal flows by Anutosh Moitra(
)
4 editions published in 1986 in English and held by 294 WorldCat member libraries worldwide
4 editions published in 1986 in English and held by 294 WorldCat member libraries worldwide
On centraldifference and upwind schemes by
R. Charles Swanson(
Book
)
5 editions published in 1990 in English and held by 146 WorldCat member libraries worldwide
A class of numerical dissipation models for centraldifference schemes constructed with second and fourthdifference terms is considered. The notion of matrix dissipation associated with upwind schemes is used to establish improved shock capturing capability for these models. In addition, conditions are given that guarantee that such dissipation models produce a TVD scheme. Appropriate switches for this type of model to ensure satisfaction of the TVD property are presented. Significant improvements in the accuracy of a central difference scheme are demonstrated by computing both inviscid and viscous transonic airfoil flows
5 editions published in 1990 in English and held by 146 WorldCat member libraries worldwide
A class of numerical dissipation models for centraldifference schemes constructed with second and fourthdifference terms is considered. The notion of matrix dissipation associated with upwind schemes is used to establish improved shock capturing capability for these models. In addition, conditions are given that guarantee that such dissipation models produce a TVD scheme. Appropriate switches for this type of model to ensure satisfaction of the TVD property are presented. Significant improvements in the accuracy of a central difference scheme are demonstrated by computing both inviscid and viscous transonic airfoil flows
High order accurate solutions of viscous problems by
Ehteshamul Md Hayder(
Book
)
4 editions published in 1993 in English and held by 109 WorldCat member libraries worldwide
4 editions published in 1993 in English and held by 109 WorldCat member libraries worldwide
Central difference TVD and TVB schemes for time dependent and steady state problems by P Jorgenson(
Book
)
4 editions published in 1992 in English and held by 107 WorldCat member libraries worldwide
4 editions published in 1992 in English and held by 107 WorldCat member libraries worldwide
Multistage schemes with multigrid for Euler and NavierStokes equations : components and analysis by
R. Charles Swanson(
Book
)
4 editions published in 1997 in English and held by 102 WorldCat member libraries worldwide
4 editions published in 1997 in English and held by 102 WorldCat member libraries worldwide
Preconditioning for numerical simulation of low Mach number threedimensional viscous turbomachinery flows by
Daniel L Tweedt(
Book
)
4 editions published in 1997 in English and held by 100 WorldCat member libraries worldwide
4 editions published in 1997 in English and held by 100 WorldCat member libraries worldwide
Construction of three dimensional solutions for the Maxwell equations by
Amir Yeffet(
Book
)
4 editions published in 1998 in English and held by 92 WorldCat member libraries worldwide
4 editions published in 1998 in English and held by 92 WorldCat member libraries worldwide
Preconditioning and the limit to the incompressible flow equations by
E Turkel(
Book
)
7 editions published in 1993 in English and Undetermined and held by 92 WorldCat member libraries worldwide
We consider the use of preconditioning methods to accelerate the convergence to a steady state for both the incompressible and compressible fluid dynamic equations. We also consider the relation between them for both the continuous problem and the finite difference approximation. The analysis relies on the inviscid equations. The preconditioning consists of a matrix multiplying the time derivatives. Hence, the steady state of the preconditioned system is the same as the steady state of the original system. For finite difference methods the preconditioning can change and improve the steady state solutions. An application to flow around an airfoil is presented. Preconditioning, Euler equations
7 editions published in 1993 in English and Undetermined and held by 92 WorldCat member libraries worldwide
We consider the use of preconditioning methods to accelerate the convergence to a steady state for both the incompressible and compressible fluid dynamic equations. We also consider the relation between them for both the continuous problem and the finite difference approximation. The analysis relies on the inviscid equations. The preconditioning consists of a matrix multiplying the time derivatives. Hence, the steady state of the preconditioned system is the same as the steady state of the original system. For finite difference methods the preconditioning can change and improve the steady state solutions. An application to flow around an airfoil is presented. Preconditioning, Euler equations
Highaccuracy compact MacCormacktype schemes for computational aeroacoustics by
R Hixon(
Book
)
3 editions published in 1998 in English and held by 90 WorldCat member libraries worldwide
3 editions published in 1998 in English and held by 90 WorldCat member libraries worldwide
Comparison of three explicit multigrimethods for the Euler and NavierStokes equations by
Rodrick V Chima(
Book
)
3 editions published in 1987 in English and held by 90 WorldCat member libraries worldwide
3 editions published in 1987 in English and held by 90 WorldCat member libraries worldwide
Pseudocompressiblity methods for the incompressible flow equations by
E Turkel(
Book
)
7 editions published in 1993 in English and held by 88 WorldCat member libraries worldwide
We consider preconditioning methods to accelerate convergence to a steady state for the incompressible fluid dynamic equations. The analysis relies on the inviscid equations. The preconditioning consists of a matrix multiplying the time derivatives. Thus the steady state of the preconditioned system is the same as the steady state of the original system. We compare our method to other types of pseudocompressibility. For finite difference methods preconditioning can change and improve the steady state solutions. An application to viscous flow around a cascade with a nonperiodic mesh is presented. Preconditioning, Incompressible equations
7 editions published in 1993 in English and held by 88 WorldCat member libraries worldwide
We consider preconditioning methods to accelerate convergence to a steady state for the incompressible fluid dynamic equations. The analysis relies on the inviscid equations. The preconditioning consists of a matrix multiplying the time derivatives. Thus the steady state of the preconditioned system is the same as the steady state of the original system. We compare our method to other types of pseudocompressibility. For finite difference methods preconditioning can change and improve the steady state solutions. An application to viscous flow around a cascade with a nonperiodic mesh is presented. Preconditioning, Incompressible equations
Review of preconditioning methods for fluid dynamics by
E Turkel(
Book
)
4 editions published in 1992 in English and held by 88 WorldCat member libraries worldwide
We consider the use of preconditioning methods to accelerate the convergence to a steady state for both the incompressible and compressible fluid dynamic equations. Most of the analysis relies on the inviscid equations though some applications for viscous flow are considered. The preconditioning can consist of either a matrix or a differential operator acting on the time derivatives. Hence, in the steady state the original steady solution is obtained. For finite difference methods the preconditioning can change and improve the steady state solutions. Several preconditioners previously discussed are reviewed and some new approaches are presented. Preconditioning, Low Mach, Euler equations
4 editions published in 1992 in English and held by 88 WorldCat member libraries worldwide
We consider the use of preconditioning methods to accelerate the convergence to a steady state for both the incompressible and compressible fluid dynamic equations. Most of the analysis relies on the inviscid equations though some applications for viscous flow are considered. The preconditioning can consist of either a matrix or a differential operator acting on the time derivatives. Hence, in the steady state the original steady solution is obtained. For finite difference methods the preconditioning can change and improve the steady state solutions. Several preconditioners previously discussed are reviewed and some new approaches are presented. Preconditioning, Low Mach, Euler equations
An effective multigrid method for highspeed flows by
R. Charles Swanson(
Book
)
5 editions published in 1991 in English and held by 87 WorldCat member libraries worldwide
We consider the use of a multigrid method with central differencing to solve the Navier Stokes equations for high speed flows. The timedependent form of the equations is integrated with a RungeKutta scheme accelerated by local time stepping and variable coefficient implicit residual smoothing. Of particular importance are the details of the numerical dissipation formulation, especially the switch between the second and fourth difference terms. Solutions are given for twodimensional laminar flow over a circular cylinder and a 15 degree compression ramp
5 editions published in 1991 in English and held by 87 WorldCat member libraries worldwide
We consider the use of a multigrid method with central differencing to solve the Navier Stokes equations for high speed flows. The timedependent form of the equations is integrated with a RungeKutta scheme accelerated by local time stepping and variable coefficient implicit residual smoothing. Of particular importance are the details of the numerical dissipation formulation, especially the switch between the second and fourth difference terms. Solutions are given for twodimensional laminar flow over a circular cylinder and a 15 degree compression ramp
Comparison of several dissipation algorithms for central difference schemes by
R. Charles Swanson(
Book
)
3 editions published in 1997 in English and held by 86 WorldCat member libraries worldwide
Several algorithms for introducing artificial dissipation into a central difference approximation to the Euler and Navier Stokes equations are considered. The focus of the paper is on the convective upwind and split pressure (CUSP) scheme which is designed to support single interior point discrete shock waves. This scheme is analyzed and compared in detail with scalar and matrix dissipation (MATD) schemes. Resolution capability is determined by solving subsonic transonic, and hypersonic flow problems. A finitevolume discretization and a multistage timestepping scheme with multigrid are used to compute solutions to the flow equations. Numerical results are also compared with either theoretical solutions or experimental data. For transonic airfoil flows the best accuracy on coarse meshes for aerodynamic coefficients is obtained with a simple MATD scheme
3 editions published in 1997 in English and held by 86 WorldCat member libraries worldwide
Several algorithms for introducing artificial dissipation into a central difference approximation to the Euler and Navier Stokes equations are considered. The focus of the paper is on the convective upwind and split pressure (CUSP) scheme which is designed to support single interior point discrete shock waves. This scheme is analyzed and compared in detail with scalar and matrix dissipation (MATD) schemes. Resolution capability is determined by solving subsonic transonic, and hypersonic flow problems. A finitevolume discretization and a multistage timestepping scheme with multigrid are used to compute solutions to the flow equations. Numerical results are also compared with either theoretical solutions or experimental data. For transonic airfoil flows the best accuracy on coarse meshes for aerodynamic coefficients is obtained with a simple MATD scheme
Preconditioning methods for lowspeed flows by
E Turkel(
Book
)
4 editions published in 1996 in English and held by 86 WorldCat member libraries worldwide
We consider the steadystate equations for a compressible fluid. For lowspeed flow, the system is stiff because the ratio of the convective speed to the speed of sound is quite small. To overcome this difficulty, we alter the time evolution of the equations but retain the same steadystate analytic equations. To achieve high numerical resolution, we also alter the artificial viscosity of the numerical scheme, which is implemented conveniently by using other sets of variables in addition to the conservative variables. We investigate the effect of the artificial dissipation within this preconditioned system. We consider both the nonconservative and conservative formulations for artificial viscosity and examine their effect on the accuracy and convergence of the numerical solutions. The numerical results for viscous threedimensional wing flows and twodimensional multielement airfoil flows indicate that efficient multigrid computations of flows with arbitrarily low Mach numbers are now possible with only minor modifications to existing compressible NavierStokes codes. The conservative formulation for artificial viscosity, coupled with the preconditioning, offers a viable computational fluid dynamics (CFD) tool for analyzing problems that contain both incompressible and compressible flow regimes
4 editions published in 1996 in English and held by 86 WorldCat member libraries worldwide
We consider the steadystate equations for a compressible fluid. For lowspeed flow, the system is stiff because the ratio of the convective speed to the speed of sound is quite small. To overcome this difficulty, we alter the time evolution of the equations but retain the same steadystate analytic equations. To achieve high numerical resolution, we also alter the artificial viscosity of the numerical scheme, which is implemented conveniently by using other sets of variables in addition to the conservative variables. We investigate the effect of the artificial dissipation within this preconditioned system. We consider both the nonconservative and conservative formulations for artificial viscosity and examine their effect on the accuracy and convergence of the numerical solutions. The numerical results for viscous threedimensional wing flows and twodimensional multielement airfoil flows indicate that efficient multigrid computations of flows with arbitrarily low Mach numbers are now possible with only minor modifications to existing compressible NavierStokes codes. The conservative formulation for artificial viscosity, coupled with the preconditioning, offers a viable computational fluid dynamics (CFD) tool for analyzing problems that contain both incompressible and compressible flow regimes
Multigrid for hypersonic viscous twoand threedimensional flows by
Institute for Computer Applications in Science and Engineering(
Book
)
5 editions published in 1991 in English and held by 86 WorldCat member libraries worldwide
We consider the use of a multigrid method with central differencing to solve the Navier Stokes equation for hypersonic flows. The timedependent form of the equations is integrated with an explicit RungeKutta scheme accelerated by local time stepping and implicit residual smoothing. Variable coefficients are developed for the implicit process that remove the diffusion limit on the time step, producing significant improvement in convergence. A numerical dissipation formulation that provides good shockcapturing capability for hypersonic flow is presented. This formulation is shown to be a crucial aspect of the multigrid method. Solutions are given for twodimensional viscous flow over a NACA 0012 airfoil and threedimensional viscous flow over a blunt biconic
5 editions published in 1991 in English and held by 86 WorldCat member libraries worldwide
We consider the use of a multigrid method with central differencing to solve the Navier Stokes equation for hypersonic flows. The timedependent form of the equations is integrated with an explicit RungeKutta scheme accelerated by local time stepping and implicit residual smoothing. Variable coefficients are developed for the implicit process that remove the diffusion limit on the time step, producing significant improvement in convergence. A numerical dissipation formulation that provides good shockcapturing capability for hypersonic flow is presented. This formulation is shown to be a crucial aspect of the multigrid method. Solutions are given for twodimensional viscous flow over a NACA 0012 airfoil and threedimensional viscous flow over a blunt biconic
A farfield nonreflecting boundary condition for twodimensional wake flows by
Jeffrey S Danowitz(
Book
)
4 editions published in 1995 in English and held by 85 WorldCat member libraries worldwide
Farfield boundary conditions for external flow problems have been developed based upon longwave perturbations of linearized flow equations about a steady state far field solution. The boundary improves convergence to steady state in singlegrid temporal integration schemes using both regulartimestepping and localtimestepping. The farfield boundary may be near the trailing edge of the body which significantly reduces the number of grid points, and therefore the computational time, in the numerical calculation. In addition the solution produced is smoother in the farfield than when using extrapolation conditions. The boundary condition maintains the convergence rate to steady state in schemes utilizing multignd acceleration. (AN)
4 editions published in 1995 in English and held by 85 WorldCat member libraries worldwide
Farfield boundary conditions for external flow problems have been developed based upon longwave perturbations of linearized flow equations about a steady state far field solution. The boundary improves convergence to steady state in singlegrid temporal integration schemes using both regulartimestepping and localtimestepping. The farfield boundary may be near the trailing edge of the body which significantly reduces the number of grid points, and therefore the computational time, in the numerical calculation. In addition the solution produced is smoother in the farfield than when using extrapolation conditions. The boundary condition maintains the convergence rate to steady state in schemes utilizing multignd acceleration. (AN)
Multigrid for hypersonic inviscid flows by
Naomi H Decker(
Book
)
4 editions published in 1990 in English and held by 85 WorldCat member libraries worldwide
We consider the use of multigrid methods to solve the Euler equations for hypersonic flow. We consider the steady state equations with a RungeKutta smoother based on the time accurate equations together with local time stepping and residual smoothing. We examine the effect of the RungeKutta coefficients on the convergence rate considering both damping characteristics and convection properties. We also show the importance of boundary conditions on the convergence rate for hypersonic flow. Also of importance of boundary conditions on the convergence rate for hypersonic flow. Also of importance are the switch between the second and fourth difference viscosity. Solutions are given for flow around a bump in a channel and flow around a biconic section. (Author) (kr)
4 editions published in 1990 in English and held by 85 WorldCat member libraries worldwide
We consider the use of multigrid methods to solve the Euler equations for hypersonic flow. We consider the steady state equations with a RungeKutta smoother based on the time accurate equations together with local time stepping and residual smoothing. We examine the effect of the RungeKutta coefficients on the convergence rate considering both damping characteristics and convection properties. We also show the importance of boundary conditions on the convergence rate for hypersonic flow. Also of importance of boundary conditions on the convergence rate for hypersonic flow. Also of importance are the switch between the second and fourth difference viscosity. Solutions are given for flow around a bump in a channel and flow around a biconic section. (Author) (kr)
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Aerodynamic noise Aerodynamic noiseMathematics Aerodynamics, Hypersonic Aerofoils AirplanesNoise Computational fluid dynamics Differential equations Differential equations, Partial Finite volume method Fluid dynamics Internal waves Inviscid flow Lagrange equations Mach number Maxwell equations Multigrid methods (Numerical analysis) NavierStokes equations Numerical analysis Problem solving RungeKutta formulas Shock waves Turbomachines Viscous flow
Alternative Names
Eli Turkel matemàtic israelià
Eli Turkel matemático israelí
Eli Turkel matemáticu israelín
Eli Turkel mathématicien israélien
Turkel, E.
Turkel, Eli
.Tẇrqel, ʾEli
Ṭwrqel, ʾEliy 1944...
אלי טורקל מתמטיקאי ישראלי
טורקל, אלי
טורקל אלי 1944....
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