Numerical attempt for capturing wing wake flows

Research output: Contribution to conferencePaper

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 languageEnglish
Pages6786-6793
Number of pages8
Publication statusPublished - 2004 Jul 1
Event42nd AIAA Aerospace Sciences Meeting and Exhibit - Reno, NV, United States
Duration: 2004 Jan 52004 Jan 8

Other

Other42nd AIAA Aerospace Sciences Meeting and Exhibit
CountryUnited States
CityReno, NV
Period04/1/504/1/8

ASJC Scopus subject areas

  • Engineering(all)

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  • Cite this

    Sawada, K., & Ohnishi, N. (2004). Numerical attempt for capturing wing wake flows. 6786-6793. Paper presented at 42nd AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, United States.