Erik Dick was born on December10, 1950 in Torhout, Belgium. He obtained a M.Sc. in Mechanical Engineering from Ghent University (Belgium) in 1973 and a Ph.D. in Computational Fluid Dynamics from the same university in 1980. From 1973 to 1991, he worked at Ghent University as researcher, senior researcher and research leader in the turbomachinery division of the Department of Mechanical Engineering. He became associate professor of thermal turbomachines and propulsion at the University of Liège (Belgium), in July 1991. He returned to Ghent University in September 1992 as associate professor and became full professor in 1995, where he taught turbomachines and computational fluid dynamics until his retirement in September 2014. His area of research is computational methods and turbulence and transition models for flow problems in mechanical engineering. He is author or co-author of about 120 papers in international scientific journals and about 220 papers at international scientific conferences. He is the recipient of the 1990 Iwan Akerman award for fluid machinery of the Belgian National Science Foundation and he is recipient of the 2002 Belgian Francqui Chair with a lecture series on simulation and modelling of complex flows at the University of Liège.
Gas-solid flow in industrial scale Circulating Fluidized Beds (CFB’s) is calculated in 3D using t... more Gas-solid flow in industrial scale Circulating Fluidized Beds (CFB’s) is calculated in 3D using the Eulerian-Eulerian approach and the Kinetic Theory of Granular Flow (KTGF). Two outlet configurations are used: a straight top outlet and a double abrupt T-outlet. The effect of the value of the restitution coefficient for particle-particle collisions on the stability of the flow is investigated. Oscillations appearing in CFB’s, are shown to be gravity waves.
Iterative solution of convection-diffusion steady flow equations is discussed. Positivity and dis... more Iterative solution of convection-diffusion steady flow equations is discussed. Positivity and discrete ellipticity are explained. Multigrid formulation of a relaxation method is outlined. The Cauchy-Riemann equations are presented. The incompressible Navier-Stokes equations are solved. Flux vector splitting and flux difference splitting for Euler equations are compared.
International Journal of Numerical Methods for Heat & Fluid Flow, 1995
A comparison of the accuracy of the central discretization scheme with artificial dissipation and... more A comparison of the accuracy of the central discretization scheme with artificial dissipation and the upwind flux‐difference TVD scheme has been made for the compressible Navier‐Stokes equations for high Reynolds number flows. First, a comparison is made on two one‐dimensional model problems. Then the schemes are compared on flat plate boundary layer flow. It is shown that a central scheme basically has poor accuracy due to the isotropic nature of the artificial dissipation. An upwind scheme decomposes the flow into different components and adapts the dissipation to the velocity of the components. The associated ansitropic dissipation results in a good accuracy. It is further discussed how a central discretization scheme with artificial dissipation can be improved at the expense of the same complexity of an upwind scheme.
International Journal of Numerical Methods for Heat & Fluid Flow, 2003
A numerical scheme that has already proved to be efficient and accurate for laminar heat transfer... more A numerical scheme that has already proved to be efficient and accurate for laminar heat transfer is extended for turbulent, axisymmetric heat transfer calculations. The extended scheme is applied to the steady‐state heat transfer of axisymmetric turbulent jets, impinging onto a flat plate. Firstly, the low‐Reynolds version of the standard k‐ε model is employed. As is well known, the classical k‐ε turbulence model fails to predict the heat transfer of impinging jets adequately. A non‐linear k‐ε model, with improved ε‐equation, yields much better results. The numerical treatment of the higher order terms in this model is described. The effect on the heat transfer predictions of a variable turbulent Prandtl number is shown to be small. It is also verified that the energy equation can be simplified, without affecting the results. Results are presented for the flow field and the local Nusselt number profiles on the plate for impinging jets with different distances between the pipe exit ...
Computers in Cardiology 1999. Vol.26 (Cat. No.99CH37004)
A 2D axisymmetrical computer model is developed describing left ventricular (LV) flow during fill... more A 2D axisymmetrical computer model is developed describing left ventricular (LV) flow during filling. The unsteady Navier-Stokes equations in a LV geometry with moving walls are solved. The relaxation and compliance of the LV wall and the fluid-wall interaction are taken into account. The method is used to simulate the filling of a canine heart. The computed results show intraventricular
Discretization of viscous incompressible and viscous low Mach number flows often leads to a syste... more Discretization of viscous incompressible and viscous low Mach number flows often leads to a system of equations which is difficult to solve. This has two reasons: first, high aspect ratio grids result in a numerically-anisotropic behaviour of the diffusive and acoustic terms and second, especially in low Mach number flow, the ratio of the eigenvalues of the inviscid system may become very high. We implemented a new discretization method, using an explicit third order discretization for the convective part, a line implicit central discretization for the acoustic part and for the diffusive part. The lines are chosen in the direction of the gridpoints with shortest connection. The preconditioned semi-implicit line method is used in multistage form because of the explicit third order discretization of the convective part. Multigrid is used as acceleration technique. It is shown in the paper that the convergence is very good, independent of the grid aspect ratio and the Mach number.
A transition model for describing bypass transition is presented. It is based on a two-equations ... more A transition model for describing bypass transition is presented. It is based on a two-equations k–ω model and a dynamic equation for intermittency factor. The intermittency factor is a multiplier of the turbulent viscosity computed by the turbulence model. Following a suggestion by Menter et al. [1], the start of transition is computed based on local variables. The choice of the Shear-Stress Transport (SST) model instead of a k–ε model is explained. The quality of the transition model, developed on flat plate test cases, is illustrated for cascades.
Results are presented for simulation of unconfined round impinging jets at noz-zle-plate distance... more Results are presented for simulation of unconfined round impinging jets at noz-zle-plate distance H/D=2 (D is the nozzle exit diameter) and three Reynolds numbers Re=5000, 23,000 and 70,000 with a k-omega based hybrid RANS/LES (Reynolds-averaged Navier-Stokes/Large Eddy Simulation), dynamic Smagorinsky LES and a RANS k-omega model. With the hybrid RANS/LES model, improved heat transfer results are obtained, when compared to RANS, in the impingement zone and in the developing wall-jet re-gion. For accurate predictions, it is necessary to sufficiently resolve the formation and development of the near-wall vortices in the developing wall jet region.
The qualities of a hybrid RANS/LES, a PANS and a PRNS model, all based on the k-omega RANS model ... more The qualities of a hybrid RANS/LES, a PANS and a PRNS model, all based on the k-omega RANS model of Wilcox (2008), are analysed for simulation of plane impinging jets at various nozzle-plate distances (H/B=10, 9.2 and 4, B is slot width) and two Reynolds numbers (Re=13,500 and 20,000).
Gas-solid flow in industrial scale Circulating Fluidized Beds (CFB’s) is calculated in 3D using t... more Gas-solid flow in industrial scale Circulating Fluidized Beds (CFB’s) is calculated in 3D using the Eulerian-Eulerian approach and the Kinetic Theory of Granular Flow (KTGF). Two outlet configurations are used: a straight top outlet and a double abrupt T-outlet. The effect of the value of the restitution coefficient for particle-particle collisions on the stability of the flow is investigated. Oscillations appearing in CFB’s, are shown to be gravity waves.
Iterative solution of convection-diffusion steady flow equations is discussed. Positivity and dis... more Iterative solution of convection-diffusion steady flow equations is discussed. Positivity and discrete ellipticity are explained. Multigrid formulation of a relaxation method is outlined. The Cauchy-Riemann equations are presented. The incompressible Navier-Stokes equations are solved. Flux vector splitting and flux difference splitting for Euler equations are compared.
International Journal of Numerical Methods for Heat & Fluid Flow, 1995
A comparison of the accuracy of the central discretization scheme with artificial dissipation and... more A comparison of the accuracy of the central discretization scheme with artificial dissipation and the upwind flux‐difference TVD scheme has been made for the compressible Navier‐Stokes equations for high Reynolds number flows. First, a comparison is made on two one‐dimensional model problems. Then the schemes are compared on flat plate boundary layer flow. It is shown that a central scheme basically has poor accuracy due to the isotropic nature of the artificial dissipation. An upwind scheme decomposes the flow into different components and adapts the dissipation to the velocity of the components. The associated ansitropic dissipation results in a good accuracy. It is further discussed how a central discretization scheme with artificial dissipation can be improved at the expense of the same complexity of an upwind scheme.
International Journal of Numerical Methods for Heat & Fluid Flow, 2003
A numerical scheme that has already proved to be efficient and accurate for laminar heat transfer... more A numerical scheme that has already proved to be efficient and accurate for laminar heat transfer is extended for turbulent, axisymmetric heat transfer calculations. The extended scheme is applied to the steady‐state heat transfer of axisymmetric turbulent jets, impinging onto a flat plate. Firstly, the low‐Reynolds version of the standard k‐ε model is employed. As is well known, the classical k‐ε turbulence model fails to predict the heat transfer of impinging jets adequately. A non‐linear k‐ε model, with improved ε‐equation, yields much better results. The numerical treatment of the higher order terms in this model is described. The effect on the heat transfer predictions of a variable turbulent Prandtl number is shown to be small. It is also verified that the energy equation can be simplified, without affecting the results. Results are presented for the flow field and the local Nusselt number profiles on the plate for impinging jets with different distances between the pipe exit ...
Computers in Cardiology 1999. Vol.26 (Cat. No.99CH37004)
A 2D axisymmetrical computer model is developed describing left ventricular (LV) flow during fill... more A 2D axisymmetrical computer model is developed describing left ventricular (LV) flow during filling. The unsteady Navier-Stokes equations in a LV geometry with moving walls are solved. The relaxation and compliance of the LV wall and the fluid-wall interaction are taken into account. The method is used to simulate the filling of a canine heart. The computed results show intraventricular
Discretization of viscous incompressible and viscous low Mach number flows often leads to a syste... more Discretization of viscous incompressible and viscous low Mach number flows often leads to a system of equations which is difficult to solve. This has two reasons: first, high aspect ratio grids result in a numerically-anisotropic behaviour of the diffusive and acoustic terms and second, especially in low Mach number flow, the ratio of the eigenvalues of the inviscid system may become very high. We implemented a new discretization method, using an explicit third order discretization for the convective part, a line implicit central discretization for the acoustic part and for the diffusive part. The lines are chosen in the direction of the gridpoints with shortest connection. The preconditioned semi-implicit line method is used in multistage form because of the explicit third order discretization of the convective part. Multigrid is used as acceleration technique. It is shown in the paper that the convergence is very good, independent of the grid aspect ratio and the Mach number.
A transition model for describing bypass transition is presented. It is based on a two-equations ... more A transition model for describing bypass transition is presented. It is based on a two-equations k–ω model and a dynamic equation for intermittency factor. The intermittency factor is a multiplier of the turbulent viscosity computed by the turbulence model. Following a suggestion by Menter et al. [1], the start of transition is computed based on local variables. The choice of the Shear-Stress Transport (SST) model instead of a k–ε model is explained. The quality of the transition model, developed on flat plate test cases, is illustrated for cascades.
Results are presented for simulation of unconfined round impinging jets at noz-zle-plate distance... more Results are presented for simulation of unconfined round impinging jets at noz-zle-plate distance H/D=2 (D is the nozzle exit diameter) and three Reynolds numbers Re=5000, 23,000 and 70,000 with a k-omega based hybrid RANS/LES (Reynolds-averaged Navier-Stokes/Large Eddy Simulation), dynamic Smagorinsky LES and a RANS k-omega model. With the hybrid RANS/LES model, improved heat transfer results are obtained, when compared to RANS, in the impingement zone and in the developing wall-jet re-gion. For accurate predictions, it is necessary to sufficiently resolve the formation and development of the near-wall vortices in the developing wall jet region.
The qualities of a hybrid RANS/LES, a PANS and a PRNS model, all based on the k-omega RANS model ... more The qualities of a hybrid RANS/LES, a PANS and a PRNS model, all based on the k-omega RANS model of Wilcox (2008), are analysed for simulation of plane impinging jets at various nozzle-plate distances (H/B=10, 9.2 and 4, B is slot width) and two Reynolds numbers (Re=13,500 and 20,000).
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