@inproceedings{oai:jaxa.repo.nii.ac.jp:00014457,
 author = {藤本, 圭一郎 and 北村, 圭一 and 嶋, 英志 and 滑, 慶則 and 山崎, 祐希 and 山本, 誠 and 浅田, 健吾 and Fujimoto, Keiichiro and Kitamura, Keiichi and Shima, Eiji and Namera, Yoshinori and Yamasaki, Yuki and Yamamoto, Makoto and Asada, Kengo},
 book = {宇宙航行の力学シンポジウム, Symposium on Flight Mechanics and Astrodynamics},
 month = {Dec},
 note = {宇宙航行の力学シンポジウム(平成20年度)(2008年12月4～5日、宇宙航空研究開発機構宇宙科学研究本部), Symposium on Flight Mechanics and Astrodynamics 2008 (December 4-5, 2008. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)), Sagamihara, Kanagawa Japan, Drag characteristics of Next-generation solid rocket motor is computationally studied for subsonic and super sonic conditions. Computed drag coefncients are compared with experiments. It is clarified that their difference is with in 10% of total, which is reasonable for conceptual aerodynamic analysis. Since difference of windward and base pressure is relatively small at subsonic condition, small change of base pressure can be result in large total drag change. For example, 1% change of base pressure based on free-stream static pressure corresponds to 20% change of total drag at Mach number 0.7. While, 5% change of base pressure corresponds to 4% change of total drag at Mach number 2.0. This result implies an importance of consideration of base pressure change induced by sting interference efect for the experimental data analysis., 資料番号: AA0064729034},
 publisher = {宇宙航空研究開発機構宇宙科学研究本部, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)},
 title = {次期固体ロケットの抵抗特性解析: 抵抗予測精度についての一考察},
 volume = {平成20年度},
 year = {2009}
}