@inproceedings{oai:jaxa.repo.nii.ac.jp:00004746,
 author = {大木, 裕介 and 佐々木, 大輔 and 中橋, 和博 and Oki, Yusuke and Sasaki, Daisuke and Nakahashi, Kazuhiro},
 book = {宇宙航空研究開発機構特別資料: 第42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2010 論文集, JAXA Special Publication: Proceedings of 42nd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2010},
 month = {Feb},
 note = {第42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2010 (2010年6月24日-25日. 米子コンベンションセンター BiG SHiP), 42nd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2010 (June 24-25,  2010. Yonago Convention Center BiG SHiP), Yonago, Tottori Japan, Sonic boom is one of critical problems should be solved in the development of future supersonic transports. Boom strength is commonly estimated based on near-field pressure signature, thus it is required to predict near-field pressure signature accurately. In this study, Shock Function is adopted for mesh refinement index since shock region can be effectively detected even at coarse mesh. Adaptive Mesh Refinement coupled with shock function is applied to an axisymmetric model for validation. It is proved that this approach is useful to improve pressure signature prediction in near field., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0064967039, レポート番号: JAXA-SP-10-012},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {ソニックブーム波形推算精度向上のためのShock Functionを用いた解適合細分化法},
 volume = {JAXA-SP-10-012},
 year = {2011}
}