Example Divisions

Transonic Flow on a Wing

The original mesh is refined automatically in the location of a standing lambda shock on this transonic wing. The yellow mesh shows the extra refinement on the surface.

Refinement Example

The white lines show the original mesh and the green lines show the refined (and redistributed) mesh. Note that the prism stacks have been directionally refined maintaining the layer structure.

Post-Refinement Example

In this example of the flow around a turbine blade, the automatic feature detection did not identify the entire leading edge and blade tip regions. To properly resolve the flow in this region, the refinement area was manually extended to include this location. The areas of the mesh that will be refined are shown in blue in the pictures below.