By W. Rodi and N. Fueyo (Eds.)
Read or Download Engineering Turbulence Modelling and Experiments 5. Proceedings of the 5th International Symposium on Engineering Turbulence Modelling and Measurements Mallorca, Spain, 16–18 September, 2002 PDF
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Additional info for Engineering Turbulence Modelling and Experiments 5. Proceedings of the 5th International Symposium on Engineering Turbulence Modelling and Measurements Mallorca, Spain, 16–18 September, 2002
CPU power has been multiplied by more than 100 in 10 years, and the memory available increased from a few hundreds KBytes to a few hundred of GBytes, this allowed very limited meshes used in 1985 (10 000 elements for a combustion chamber) to meshes up to 2 millions elements today, or even more, used for underhood modelling or external aerodynamics. The progress concerns also the softwares. In the early times, we had to deal with structured hexahedron meshes (example: KIVA) for complex geometries and today most of the softwares allow tetrahedral meshes.
The eddy viscosity is proportional to the square of a length scale and to the rate of flow deformation. The length scale must be prescribed empirically and depends on the characteristics of the flow. This model is applied when the flow has a privileged direction: such as boundary layer, shear stress, etc. The only known application was inlet airflow simulation, which was not satisfactory. More generally, it is unsuitable for complex flows because it is very difficuk to estimate the distribution of the mixing length One-equation models: such as k-L model.
50 Two-dimensional blade boundary layers are beyond the ability of current turbulence models The simplest picture of two-dimensional boundary layer development on a single turbomachinery blade is as follows: • laminar boundary layer forms at the leading edge stagnation point • laminar to turbulent transition occurs somewhere near the onset of adverse pressure gradients • turbulent boundary layer flow occursfiirtherdownstream on the surface. Despite its simplicity this is more complex than most CFD codes can calculate.