@techreport{oai:jaxa.repo.nii.ac.jp:00045393,
 author = {高橋, 侔 and 藤枝, 郭俊 and 岩崎, 昭人 and 藤田, 敏美 and 斉藤, 雅樹 and TAKAHASHI, Hitoshi and FUJIEDA, Hirotoshi and IWASAKI, Akihito and FUJITA, Toshimi and SAITO, Masaki},
 month = {Dec},
 note = {航空宇宙技術研究所ではSTOL実験機「飛鳥」の研究開発と共に,STOL-CADプログラムの開発,改良を行ってきた。このCADプログラムの適用範囲を2発,3発USB機へ広げるのに必要な空力データ取得を目的として,既存の4発型USB半截模型を双発型に改修して,風洞試験を実施した。本報告は同模型形態での各種空力要素に対する空力特性を検討した結果について述べる。, In parallel with the research and development conducted by the National Aerospace Laboratory (NAL) on the experimental aircraft ″ASKA″, a short takeoff and landing (STOL)-Computer Aided Design (CAD) program for four-engine upper surface blowing (USB) aircraft was developed and refined. To apply this CAD program to twin-and three-engine USB aircraft, aerodynamic data must be acquired for twin-engine USB aircraft. This led to the present study which modified the existing four-engine USB semi-span model into a twin-engine model and subsequently conducted low-speed wind tunnel tests. Resultant aerodynamic characteristics of the numerous aerodynamic elements included in this model are described., 資料番号: NALTR1134000, レポート番号: NAL TR-1134},
 title = {双発USB半截模型風洞試験},
 year = {1991}
}