Abstract
Numerical attempts are made to capture wing wake flows accurately. The wing wake region and the separated vortex from the delta wing are successfully identified as the coexisting region of two gases. Flux modifications are made in the coexisting region to sharply resolve the slip surface. In the calculation of wing wake flow from a wing section, it is found that effect of flux modification appears only in the Euler simulations where velocity slip along the wing wake is large. However, it is shown that flux modification can also give negative effect on the flowfield. For 3D delta wing, it is suggested that the present scheme can resolve the leading edge separated vortex more sharply.
| Original language | English |
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| Pages | 6786-6793 |
| Number of pages | 8 |
| Publication status | Published - 2004 |
| Event | 42nd AIAA Aerospace Sciences Meeting and Exhibit - Reno, NV, United States Duration: 2004 Jan 5 → 2004 Jan 8 |
Conference
| Conference | 42nd AIAA Aerospace Sciences Meeting and Exhibit |
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| Country/Territory | United States |
| City | Reno, NV |
| Period | 04/1/5 → 04/1/8 |