Abstract
To improve efficiency of CFD analysis, we develop an automatic and fast grid generator, HexaGrid, that produces Cartesian/prism hybrid grids. We applied HexaGrid for the NASA common research model employed for the fourth drag prediction workshop (DPW4). We investigated the grid dependency of the separated flow at attack angle of 4°. In particular, we focus on the effect of wake resolution behind the main wing. The grid in the wake region was refined using the refinement box of HexaGrid. The wake is smeared for the original grid, whereas it is clearly captured over the span for the grid with refinement box. However, the side-of-body separation bubble and its wake are not changed significantly. Therefore, the force and moment are almost same. Finally, although the refinement box does not change the result for this problem, it is useful for the problem that includes the flow interaction between main and tail wings.
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