@inproceedings{oai:jaxa.repo.nii.ac.jp:00003238,
 author = {近藤, 賢 and 上野, 篤史 and 平野, 義鎮 and 野口, 正芳 and 牧野, 好和 and 石川, 敬掲 and Kondo, Satoshi and Ueno, Atsushi and Hirano, Yoshiyasu and Noguchi, Masayoshi and Makino, Yoshikazu and Ishikawa, Hiroaki},
 book = {宇宙航空研究開発機構特別資料: 第49回流体力学講演会/第35回航空宇宙数値シミュレーション技術シンポジウム論文集, JAXA Special Publication: Proceedings of the 49th Fluid Dynamics Conference / the 35th Aerospace Numerical Simulation Symposium},
 month = {Dec},
 note = {第49回流体力学講演会/第35回航空宇宙数値シミュレーション技術シンポジウム (2017年6月28日-34日. 国際オリンピック記念青少年総合センター), 渋谷区, 東京, 49th Fluid Dynamics Conference /the 35th Aerospace Numerical Simulation Symposium (June 28-30, 2017. National Olympics Memorial Youth Center), Shibuya-ku, Tokyo, Japan, The demand of Supersonic Transport (SST) is increasing globally. Some companies have announced their program for developing civil supersonic airplanes and the International Civil Aviation Organization (ICAO) has started developing the sonic boom standard for supersonic overland flight. Second AIAA Sonic Boom Prediction Workshop (SBPW2) has been held in January 2017 to assess the state of the art for predicting sonic boom. Japan Aerospace Exploration Agency (JAXA) designed a simple low boom configuration named 'JAXA Wing Body (JWB)' and provided it to the workshop for one of the test cases of SBPW2. For the validation of sonic boom prediction method, the supersonic wind-tunnel test of the JWB model was carried out at JAXA's supersonic wind-tunnel. This paper reports the development of an aeroelastic deforming estimation tool of the main wing in wind tunnel test and the results of CFD analysis for prediction of near-field sonic boom signature with aeroelastic deformation effects., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1730011004, レポート番号: JAXA-SP-17-004},
 pages = {39--45},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {ソニックブーム推算手法検証風洞試験における主翼空力弾性変形効果},
 volume = {JAXA-SP-17-004},
 year = {2017}
}