Eli Turkel
Tel Aviv University, Applied Mathematics, Faculty Member
Research Interests:
Research Interests:
Preconditioners for hyperbolic systems are numerical artifacts to accelerate the convergence to a steady state. In addition, the preconditioner should also be included in the artificial viscosity or upwinding terms to improve the accuracy... more
Preconditioners for hyperbolic systems are numerical artifacts to accelerate the convergence to a steady state. In addition, the preconditioner should also be included in the artificial viscosity or upwinding terms to improve the accuracy of the steady state solution. For time dependent problems we use a dual time stepping approach. The preconditioner affects the convergence rate and the accuracy of the subiterations within each physical time step. We consider two types of local preconditioners: Jacobi and low speed preconditioning. We can express the algorithm in several sets of variables while using only the conservation variables for the flux terms. We compare the effect of these various variable sets on the efficiency and accuracy of the scheme.
Research Interests:
We consider the steady state equations for a compressible fluid. For low speed flow the system is stiff since the ratio of the convective speed to the speed of sound is very small. To overcome this difficulty we alter the time dependency... more
We consider the steady state equations for a compressible fluid. For low speed flow the system is stiff since the ratio of the convective speed to the speed of sound is very small. To overcome this difficulty we alter the time dependency of the equations while retaining the same steady state operator. In order to achieve high numerical resolution we also alter the artificial dissipation (or Roe matrix) of the numerical scheme. The definition of preconditioners and artificial dissipation terms can be formulated conveniently by using other sets of dependent variables rather than the conservation variables. The effects of different preconditioners, artificial dissipation and grid density on accuracy and convergence to the steady state of the numerical solutions are presented in detail. The numerical results obtained for inviscid and viscous two-and three-dimensional flows over external aerodynamic bodies indicate that efficient multigrid computations of flows with very low Mach numbers are now possible. 0 1997 Elsevier Science Ltd.
Research Interests:
Research Interests:
Research Interests:
Research Interests:
Research Interests:
Research Interests:
Research Interests:
Research Interests:
Three explicit multigrid methods, Ni's method, Jameson's finite-volume method, and a finite-difference method based on Brandt's work, are described and compared for two model problems. All three methods use an explicit multistage... more
Three explicit multigrid methods, Ni's method, Jameson's finite-volume method, and a finite-difference method based on Brandt's work, are described and compared for two model problems. All three methods use an explicit multistage Runge-Kutta scheme on the fine grid, and this scheme is also described. Convergence histories for inviscid flow over a bump in a channel for the fine-grid scheme alone show that convergence rate is proportional to Courant number and that implicit residual smoothing can significantly accelerate the scheme. Ni's method was slightly slower than the implicitly-smoothed scheme alone. Brandt's and Jameson's methods are shown to be equivalent in form but differ in their node versus cell-centered implementations. They are about 8.5 times faster than Ni's method in terms of CPU time. Results for an oblique shock/boundary layer interaction problem verify the accuracy of the finite-difference code. All methods slowed considerably on the stretched viscous grid but Brandt's method was still 2.1 times faster than Ni's method.
Research Interests:
The behavior of a sound in a jet was investigated. It is verified that the far-field acoustic power increased with flow velocity for the lower and medium frequency range. Experimentally, an attenuation at higher frequencies is also... more
The behavior of a sound in a jet was investigated. It is verified that the far-field acoustic power increased with flow velocity for the lower and medium frequency range. Experimentally, an attenuation at higher frequencies is also observed. This increase is found numerically to be due primarily to the interactions between the mean vorticity and the fluctuation velocities. Spectral decomposition of the real time data indicates that the power increase occurs in the low and middle frequency range, where the local instability waves have the largest spatial growth rate. The connection between this amplification and the local instability waves is discussed.
Research Interests:
Results obtained from a series of adiabatic and dissipative codes are described which exploit the Grad-Hogan theory of classical transient diffusion and skin penetration. The models include two-dimensions and axial symmetry, a variety of... more
Results obtained from a series of adiabatic and dissipative codes are described which exploit the Grad-Hogan theory of classical transient diffusion and skin penetration. The models include two-dimensions and axial symmetry, a variety of constraints such as specified plasma volume, toroidal and poloidal currents and fluxes, free boundaries in vacuum and force free field, limiters, etc., a variety of topologies, including time-dependent changes of topology (isolation, tearing, annihilation of islands). The principal physical results are that, under appropriate circumstances, there is significant quantitative classical disagreement with 'classical' (Pfirsch-Schlueter) diffusion and classical skin effect (current penetration). The chief numerical achievements are a family of accurate and efficient algorithms and codes which are useful in their own right and should also provide a basis for a new generation of plasma-modeling, curve-fitting codes (with added atomic physics, radiation, and anomaly factors), but with the geometry and time-dependence treated realistically.
Research Interests:
Research Interests:
The present 2D simulations of plane and axisymmetric jets, which are relevant to current efforts to suppress the jet exhaust noise of prospective high-speed civil transports, were conducted by solving full Navier-Stokes equations by means... more
The present 2D simulations of plane and axisymmetric jets, which are relevant to current efforts to suppress the jet exhaust noise of prospective high-speed civil transports, were conducted by solving full Navier-Stokes equations by means of a high-order finite-difference scheme. The results obtained, which were able to generate the correct mode shape after an adjustment region of about 10 diameters,
Research Interests:
Research Interests:
Research Interests:
ABSTRACT
Research Interests:
Research Interests:
Research Interests:
... References [1] Anderson, W., Kyle, Thomas, JL, van Leer, B., Comparison of Finite Volume Flux Vector Splittings for the Euler Equations, AIAA J., Vol. 24, pp. 1453-1460 (1986). [2] Caughey, DA, Turkel, E., Effects of Numerical ...
ABSTRACT The effects of numerical dissipation upon solutions to the Euler equations are considered, and results for transonic flows past airfoils are presented to demonstrate the effects of the dissipative terms. The equations are... more
ABSTRACT The effects of numerical dissipation upon solutions to the Euler equations are considered, and results for transonic flows past airfoils are presented to demonstrate the effects of the dissipative terms. The equations are approximated using a finite-volume spatial approximation with added dissipation provided by an adaptive mixture of second and fourth differences. The resulting difference equations are solved using either an explicit multistage Runge-Kutta method or a diagonalized implicit method. It is found that errors in surface values can be introduced by the averaging required to calculate derived quantities of interest.
Research Interests:
The present 2D simulations of plane and axisymmetric jets, which are relevant to current efforts to suppress the jet exhaust noise of prospective high-speed civil transports, were conducted by solving full Navier-Stokes equations by means... more
The present 2D simulations of plane and axisymmetric jets, which are relevant to current efforts to suppress the jet exhaust noise of prospective high-speed civil transports, were conducted by solving full Navier-Stokes equations by means of a high-order finite-difference scheme. The results obtained, which were able to generate the correct mode shape after an adjustment region of about 10 diameters, are in good agreement with linear-theory predictions of the growth of instability waves.
Research Interests:
We consider fourth order accurate compact schemes for numerical solutions to the Maxwell equations. We use the same mesh stencil as used in the standard Yee scheme. In particular extra information over a wider stencil is not required.... more
We consider fourth order accurate compact schemes for numerical solutions to the Maxwell equations. We use the same mesh stencil as used in the standard Yee scheme. In particular extra information over a wider stencil is not required. Hence, it is relatively easy to modify an existing code based on the Yee algorithm to make it fourth order accurate. Also, a staggered mesh makes the boundary treatment easier. Finally, a staggered grid system gives a lower error than a non-staggered system
Research Interests:
ABSTRACT We introduce the time reversed absorbing conditions (TRAC) in time reversal methods. These new boundary conditions enable one to “recreate the past”without knowing the source that has emitted the signals that are back-propagated.... more
ABSTRACT We introduce the time reversed absorbing conditions (TRAC) in time reversal methods. These new boundary conditions enable one to “recreate the past”without knowing the source that has emitted the signals that are back-propagated. This new method does not rely on any a priori knowledge of the physical properties of the inclusion. We prove an energy es- timate for the resulting non-standard boundary value prob- lem. Numerical tests are presented in two dimensions for the wave and the Helmholtz equation. In particular the TRAC method is applied to the differentiation between a single in- clusion and a two close inclusion case. This technique is fairly insensitive with respect to noise in the data.