@inproceedings{oai:jaxa.repo.nii.ac.jp:00004255,
 author = {牧野, 好和 and 野口, 正芳 and 村上, 桂一 and 橋本, 敦 and 金森, 正史 and 石川, 敬掲 and 牧本, 卓也 and 内田, 貴也 and 大林, 茂 and 今泉, 貴博 and 鈴木, 角栄 and 豊田, 篤 and 佐宗, 章弘 and Makino, Yoshikazu and Noguchi, Masayoshi and Murakami, Keiichi and Hashimoto, Atsushi and Kanamori, Masashi and Ishikawa, Hiroaki and Makimoto, Takuya and Uchida, Takaya and Obayashi, Shigeru and Imaizumi, Takahiro and Suzuki, Kakuei and Toyoda, Atsushi and Sasoh, Akihiro},
 book = {宇宙航空研究開発機構特別資料, JAXA Special Publication: Proceedings of 44th Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2012},
 month = {Mar},
 note = {第44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2012 (2012年7月5日-6日. 富山国際会議場大手町フォーラム), 富山市, 富山県, 44th Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2012 (July 5-6, 2012. Toyama International Conference Center), Toyama Japan, Some numerical analysis tools for predicting near-field pressure signatures of a supersonic airplane are validated with wind tunnel test data and ballistic range test data. Two model configurations of the first phase of JAXA’s low-sonic-boom concept demonstration project(DSEND#1) are used in this study. Five kinds of　numerical analysis tools, a panel analysis with aging modification, an axisymmetric Euler　CFD, an unstructured　grid Euler CFD, a structured/unstructured overset grids Euler CFD, and a hexagrid Euler CFD, are applied to　these ｍodels for predicting their near-field pressure signatures at Mach number of 1.4 and 1.7. The predicted signatures are compared with the supersonic wind tunnel data of the 5% models and the ballistic range data of the 1.6% models., 著者人数: 13名, 形態: カラー図版あり, Number of authors: 13, Physical characteristics: Original contains color illustrations, 資料番号: AA0061958015, レポート番号: JAXA-SP-12-010},
 pages = {89--94},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {D-SEND#1 形状に対する機体近傍場圧力波形推算手法検証},
 volume = {JAXA-SP-12-010},
 year = {2013}
}