@inproceedings{oai:jaxa.repo.nii.ac.jp:00006196,
 author = {桑原, 邦郎 and 小紫, 誠子 and Kuwahara, Kunio and Komurasaki, Satoko},
 book = {宇宙航空研究開発機構特別資料: 境界層遷移の解明と制御研究会講演論文集　第35回・第36回, JAXA Special Publication: Proceedings of the 35th and 36th JAXA Workshops on Investigation and Control of Boundary-Layer Transition},
 month = {Feb},
 note = {In the present paper, a simulation of a subsonic flow around airfoil NACA0012 is attacked. Computations are done at angles of attack 8 deg to 18 deg and at the Reynolds number of 106 based on the chord length. In this computation, the incompressible Navier-Stokes equations are solved by the multi-directional finite-difference method with using an O-type grid system. For high Reynolds number flow, no explicit turbulence models are employed, but a third order upwind scheme is adopted. On the far boundary, circulation is corrected consistently, and a periodic boundary condition is used in the spanwise direction. Results show that circulation correction on the far boundary has effect on the flow field, especially, it increases the value of Cl at low angles of attack., 資料番号: AA0049208014, レポート番号: JAXA-SP-05-012},
 pages = {43--46},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {Simulation of a flow around an airfoil with a circulation boundary condition},
 volume = {JAXA-SP-05-012},
 year = {2006}
}