JAXA高揚力装置風洞模型のCFD解析
| Autor: | Nakayama, Ryo, Kuroda, Masafumi, Yamazaki, Wataru, Matsushima, Kisa, Nakahashi, Kazuhiro |
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| Jazyk: | japonština |
| Rok vydání: | 2008 |
| Předmět: |
境界層遷移
flow distribution 流れの分布 wind tunnel model high-lift device 計算流体力学 圧力分布 computational fluid dynamics 風洞試験 空力抵抗 pressure distribution turbulence model Physics::Fluid Dynamics passenger aircraft aerodynamic characteristic 風洞模型 旅客機 aerodynamic drag 高揚力装置 乱流モデル 空力特性 航空機設計 wind tunnel test boundary layer transition aircraft design |
| Zdroj: | 宇宙航空研究開発機構特別資料: 第39回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2007論文集 = JAXA Special Publication: Proceedings of 39th Fluid Dynamics Conference/Aerospace Numerical Simulation Symposium 2007. :184-189 |
| ISSN: | 1349-113X |
| Popis: | In this study, CFD (Computational Fluid Dynamics) analysis is performed on a JAXA 3D High-lift Configuration. The main object is to assess and improve the reliability in simulating the flow around High-Lift configuration. The lift prediction shows qualitatively good agreement with the experiment, but the accuracy of lift prediction has the matter on account of prediction around maximum lift and lift slope. Drag is estimated lager than the experiment consistently. Applying UMUSCL (Unstructured Monotone Upstream-centered Schemes for Conservation Laws), computational results show improvement in lift and drag predictions as result of spurious drag decrease. Increasing the mesh density, the large separation on flap and both lift and drag decrease are computed. The scale of separation of flap is sensitive to (especially surface) mesh resolution around flap, and affects wing circulation. Consequently, the pressure distribution is changed and predicted pitching moment is improved. Using SST (SuperSonic Transport) turbulence model, all aerodynamic coefficients come to the experimental data compared to the case of SA (Spalart-Allmaras) turbulence model. These results are also caused by the large separation on flap. The prediction of the separation on flap is important to accurate prediction of aerodynamic forces. 資料番号: AA0063742030 レポート番号: JAXA-SP-07-016 |
| Databáze: | OpenAIRE |
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