@inproceedings{oai:jaxa.repo.nii.ac.jp:00006563,
 author = {畠山, 望 and 入江, 智洋 and 井上, 督 and Hatakeyama, Nozomu and Irie, Tomohiro and Inoue, Osamu},
 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33回・第34回, JAXA Special Publication: Proceedings of the 33rd and 34th JAXA Workshops on Investigation and Control of Boundary-Layer Transition},
 month = {Jan},
 note = {The sound radiated from an airfoil (NACA0012) in a uniform flow is studied using direct numerical simulation (DNS). The two-dimensional compressible Navier-Stokes equations are solved by a 6th-order-accurate Pade type compact scheme and a 4th-order-accurate Runge-Kutta scheme. The Reynolds number based on the airfoil chord length is prescribed to be 5,000, and the Mach number of the uniform flow to be 0.2. The angle of attack is varied from 5 deg to 8 deg. The results show that dipole sounds are generated in accordance with the oscillations of lift and drag forces due to the vortex shedding. As the angle of attack varies, the flow structure near the airfoil is affected, and the generated sounds change in response to the transition of the vortex motion around the airfoil., 資料番号: AA0047776009, レポート番号: JAXA-SP-04-002},
 pages = {29--30},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {翼型による空力音の2次元直接数値計算},
 volume = {JAXA-SP-04-002},
 year = {2005}
}