@inproceedings{oai:jaxa.repo.nii.ac.jp:00004748,
 author = {石川, 敬掲 and 牧野, 好和 and 吉田, 憲司 and 大平, 啓介 and Ishikawa, Hiroaki and Makino, Yoshikazu and Yoshida, Kenji and Ohira, Keisuke},
 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 due to a supersonic airplane is the one of the most serious problems to be solved for supersonic overland flight. Prediction of the sonic-boom on the ground is important to design a low-boom supersonic airplane. Structured/unstructured overset grids method is developed to estimate the ground the sonic-boom and evaluate the effects of the low-boom design concepts. The unstructured mesh CFD analysis solves only around the airplane. Then the structured mesh CFD analysis solves the near field pressure field using the results of unstructured mesh CFD analysis. The purpose of this overset grids method is to predict the near-field pressure signatures accurately and efficiently which are used to estimate the sonic-boom on the ground. In this paper, the structured/unstructured overset grids method is applied to the Darden's low-boom axisymmetric shape and Concorde type airplane., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0064967041, 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 = {構造／非構造重合格子法を用いたコンコルド模擬形状のソニックブーム解析},
 volume = {JAXA-SP-10-012},
 year = {2011}
}