Application of local correlation-based transition model to flows around wings

Takashi Misaka, Shigeru Obayashi

研究成果: Conference contribution

23 被引用数 (Scopus)

抄録

The γ-Reθ transition model with a newly developed transition correlation set is applied to the stall angle prediction of thin airfoil, NACA 64A006. Empirical correlations used in the present model are developed based on literatures and numerical experiments and validated by skin friction coefficients on flat plate for several free stream turbulent intensities: T3 test cases for bypass transition regime and Schubauer& Klebanof for natural transition regime. For validation of separated flow transition, T3LC test case which uses coupland flat plate are computed and have a good agreement with experimental results of skin friction coefficient. The present γ-Reθ transition model is applied to stall angle prediction of NACA 64A006 airfoil to investigate the effect of boundary layer transition on massively separated flow problem within the framework of Reynolds-averaged Navier-Stokes computation. The results show that the γ-Reθ transition model improves the prediction capability of stall angle.

本文言語English
ホスト出版物のタイトルCollection of Technical Papers - 44th AIAA Aerospace Sciences Meeting
出版社American Institute of Aeronautics and Astronautics Inc.
ページ10973-10983
ページ数11
ISBN(印刷版)1563478072, 9781563478079
DOI
出版ステータスPublished - 2006
イベント44th AIAA Aerospace Sciences Meeting 2006 - Reno, NV, United States
継続期間: 2006 1月 92006 1月 12

出版物シリーズ

名前Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting
15

Other

Other44th AIAA Aerospace Sciences Meeting 2006
国/地域United States
CityReno, NV
Period06/1/906/1/12

ASJC Scopus subject areas

  • 宇宙惑星科学
  • 航空宇宙工学

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