@inproceedings{oai:jaxa.repo.nii.ac.jp:00005440,
 author = {郭, 東潤 and 吉田, 憲司 and 徳川, 直子 and 石川, 敬掲 and Kwak, Dong-Youn and Yoshida, Kenji and Tokugawa, Naoko and Ishikawa, Hirotaka},
 book = {宇宙航空研究開発機構特別資料: 小型超音速実験機（ロケット実験機）飛行実験データ解析完了報告, JAXA Special Publication},
 month = {Feb},
 note = {小型超音速実験機（ロケット実験機）飛行実験データ解析完了報告会(平成20年7月10日. 東京大学山上会館), Flight test of a supersonic experimental airplane was performed by Japan Aerospace Exploration Agency to improve advanced aerodynamic design technologies for the next generation SST. The experimental airplane was designed to reduce the drag on a supersonic cruise condition. Surface pressure distributions, boundary layer transition locations and aerodynamic forces in the flight test were obtained to demonstrate the aerodynamic design methods and tools. The flight test results evaluated by comparing with the prediction results obtained by CFD based optimum design tools. The flight test results relatively corresponded to the CFD results. Aerodynamic design concepts for drag reduction were demonstrated qualitatively and quantitatively by the NEXST-1 flight test., 形態: カラー図版あり, 資料番号: AA0064239004, レポート番号: JAXA-SP-08-008},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {飛行実験による空力設計コンセプトの検証},
 volume = {JAXA-SP-08-008},
 year = {2009}
}