This paper discusses the use of the vorticity confinement method coupled with the unstructured grid approach to simulate vortical flows. The method is evaluated by several vortical flow computations of the leading-edge separation vortices on delta wings and the wing tip vortices of NACA0012 wing. It is shown that the vorticity confinement can keep the vorticity away from the numerical diffusion effectively. Although further study to reduce the dependency of the confinement coefficient on the grid density is required, the present results indicate the possibility of accurate vortical flow computations by the vorticity confinement method coupled with unstructured and adaptive refinement grids.
|出版ステータス||Published - 2001 12月 1|
|イベント||39th Aerospace Sciences Meeting and Exhibit 2001 - Reno, NV, United States|
継続期間: 2001 1月 8 → 2001 1月 11
|Other||39th Aerospace Sciences Meeting and Exhibit 2001|
|Period||01/1/8 → 01/1/11|
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