http://swrc.ontoware.org/ontology#InProceedings
遷音速フラッターシミュレーションにおける陰解法の時間刻み幅選定基準について
ja
航空機設計
空力特性
遷音速フラッタ
遷音速飛行
CFD
非定常空気力学
翼型振動
Baldwin-Lomax乱流モデル
陰解法
時間刻み幅
寺島 洋史
藤井 孝蔵
Terashima Hiroshi
Fujii Kozo
宇宙航空研究開発機構
Japan Aerospace Exploration Agency (JAXA)
宇宙航空研究開発機構特別資料: 航空宇宙数値シミュレーション技術シンポジウム2004論文集
JAXA-SP-04-012
105-110
2005-03-25
One criterion that determines time stepping size in the implicit time integration method is given for accurate and effective transonic flutter simulations. Transonic flows over two-dimensional forced oscillating airfoils with several reduced frequencies are first investigated for constructing a criterion for selecting the time stepping size, and then two and three-dimensional transonic flutter simulations are performed for evaluating the criterion. Results for the forced oscillating airfoil indicate that unsteady aerodynamic forces converge in a constant value as the time stepping size decreases and the time stepping size required the convergence of unsteady aerodynamic force depends on the reduced frequency. From these results, it turns out that 4,000 integration steps during one cycle of airfoil oscillations are enough for the estimation of the unsteady aerodynamic forces at any reduced frequency. The time stepping size is automatically decided by setting 4,000 integration steps during one cycle of airfoil oscillations. Results for two and three-dimensional transonic flutter simulations show that flutter boundaries can be accurately and effectively calculated based on the criterion.
1349-113X
AA11984031
資料番号: AA0048469017
レポート番号: JAXA-SP-04-012