Numerical simulation has been performed corresponding to recent experiment around delta wings with sharp and blunt leading edges at NASA Langrey Research Center, which indicates the second primary vortex and quantitative Reynolds-number effects. Three one-equation turbulence models are examined on the unstructured hybrid mesh and the modified Spalart-Allmaras turbulence model is found most effective to capture a complex vortex structure. The adaptive mesh refinement method at a vortex center is also applied. Visualization of the computational results suggests that the second primary vortex may be a developing share layer merging to an open separation of the primary vortex. Not only the volume-mesh refinement but also the surface-mesh refinement is found important to capture Reynolds-number effects around a delta wing with a blunt leading edge.
|出版ステータス||Published - 2004|
|イベント||42nd AIAA Aerospace Sciences Meeting and Exhibit - Reno, NV, United States|
継続期間: 2004 1 5 → 2004 1 8
|Other||42nd AIAA Aerospace Sciences Meeting and Exhibit|
|Period||04/1/5 → 04/1/8|
ASJC Scopus subject areas