Hey,

when using the boundary layer tool in Gambit to mesh the near wall region of an aerofoil I experience problems at the trailing edge. The x-direction size of the first cell downstream of the trailing edge appears to be equal to the y-direction cell size along the surface. For y+<5, the latter is very small, i.e. 1e-5, which means that the spacing of the cells in the x-direction downstream of the trailing edge is equally small. This, in turn, renders problems at the interface of the boundary layer and the outer region when using an unstructured mesh - the resolution is poor, skew angles etc.

Does anyone know how to change the configuration, so that the x-direction size of the cells downstream of the trailing edge can be increased (and is not equal to the y-direction size of the cells along the aerofoil surface)?

Many thanks for your comments in advance,

CC

It's difficulty by gambit.If you can send your model through Email,I can try it for you!