フラッターシミュレーションに向けた振動翼周り流れの信頼性評価
| Autor: | Terashima, Hiroshi, Fujii, Kozo |
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| Jazyk: | japonština |
| Rok vydání: | 2002 |
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| Zdroj: | 航空宇宙技術研究所特別資料: 航空宇宙数値シミュレーション技術シンポジウム2001論文集 = Special Publication of National Aerospace Laboratory: Proceedings of Aerospace Numerical Simulation Symposium 2001. 53:285-290 |
| ISSN: | 0289-260X |
| Popis: | Transonic flows over the NACA64A010 airfoil oscillating in pitch about its one-quarter chord are numerically investigated for the assessment of the flow solver to predict the accurate unsteady aerodynamics forces. The effect of the outer boundary region and time accuracy in the implicit method such as LU-SGS time integration method is also described in this paper. Results at Mach number 0.8 over the airfoil oscillating with the reduced frequency of about 0.2 are compared with experimental data, respectively. The computed results with aft-shock attached flow show the importance of the computational domain and the implementation of the inner iteration method to the implicit time integration algorithm. For the case of shock induced separation flows, the computed results disagree with the experimental results due to the effect of the turbulence modeling, even with the increased time accuracy. 資料番号: AA0032819049 レポート番号: NAL SP-53 |
| Databáze: | OpenAIRE |
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