|December 8, 2008, 05:43||
Meshing trailing edge of aerofoil
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,
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