@inproceedings{oai:jaxa.repo.nii.ac.jp:00005613,
 author = {田村, 明紀 and 蔦原, 道久 and 片岡, 武 and 青山, 剛史 and Yang, Choongmo and Tamura, Akinori and Tsutahara, Michihisa and Kataoka, Takeshi and Aoyama, Takashi and Yang, Choongmo},
 book = {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},
 month = {Feb},
 note = {Parallel blade-vortex interactions have been calculated using the finite difference lattice Boltzmann method of the compressible Euler model. The perturbed discrete Boltzmann equation based on a prescribed vortex method has been proposed in order to prevent a vortex from diffusing by numerical dissipation. The discretization of the governing equation is based on a second order accurate explicit Runge-Kutta time integration and a fifth order accurate upwind scheme which includes additional terms to capture shock waves clearly. Transonic flow around an airfoil without vortexes has been simulated to validate the perturbed discrete Boltzmann equation system. A surface pressure distribution and pressure contour lines around the airfoil have been compared with other numerical data, and good agreements have been obtained. As a simple model of parallel blade-vortex interaction, two-dimensional blade-vortex interaction has been calculated using the proposed numerical method. An instantaneous pressure coefficient, a time history of a lift coefficient and patterns of acoustic waves have been compared with other numerical results, and agreed with them very well. Mechanism of noise generation has been also captured from numerical results. Three-dimensional calculations of parallel blade-vortex interaction have been performed using the present numerical procedure. Time variations of surface pressure distributions have been compared with Euler calculation and experimental data, and good agreements have been obtained., 資料番号: AA0063742007, レポート番号: JAXA-SP-07-016},
 pages = {39--44},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {差分格子ボルツマン法によるBVIの数値解析},
 volume = {JAXA-SP-07-016},
 year = {2008}
}