@techreport{oai:jaxa.repo.nii.ac.jp:00041133,
 author = {高橋, ひとし and 奥山, 政広 and 藤枝, 郭俊 and 藤田, 敏美 and 岩崎, 昭人 and Takahashi, Hitoshi and Okuyama, Masahiro and Fujieda, Hirotoshi and Fujita, Toshimi and Iwasaki, Akihito},
 month = {Nov},
 note = {STOL実験機「飛鳥」は国産中型輸送機C-1からUSB方式STOL機に改造されたが、その設計において、かなりの制約が設けられている。そのため、STOL機として必ずしも最適な空力形状をしているわけではない。そこでSTOL実験機の開発過程で得られた成果を反映して整備されたSTOL-CAD(コンピューター支援設計)プログラムを用いて、150人乗り程度のターボ･ジェット機に適すると思われる主翼を設計し、本主翼を有する半截模型(CAD模型)を製作し、STOL機を構成する空力要素の最適形状を求めるため、風洞試験を実施した。本資料はこれら風洞試験結果の第2報であり、本結果において、CAD模型は「飛鳥」模型に比べて、大幅な空力特性の改善、機体重量の軽減の可能性を得ることができた。, The Quiet Short Take-Off and Landing (QSTOL) Experimental Aircraft 'ASKA' has been researched and developed by the National Aerospace Laboratory (NAL). The 'ASKA' was based upon the airframe of the home produced C-1 tactical transport which was modified into the Upper Surface Blowing (USB) -powered high-lift STOL aircraft. The wing configuration, however, was not changed. Therefore, this Experimental Aircraft does not always have the optimum configuration of a USB-type aircraft. So the improvement of the aerodynamic characteristics of the STOL Aircraft was tried. This paper describes the investigations which have been conducted to improve the aerodynamic characteristics of a subsonic jet transport semi-span model with an Upper Surface Blown Flap system which has been newly designed using the NAL STOL-CAD (computer Aided Design) program. The model had an 8.2 deg swept wing of aspect ratio 10.0 and four turbofan engines with short USB nozzles. The tests were conducted in the NAL 2 x 2 m Gust Wind Tunnel with closed section and results were obtained for several flap and slat deflections at jet momentum coefficients from 0 to 1.85. Compared with the aerodynamic characteristics of the 'ASKA' model, it was determined that the airframe weight can be reduced and the aerodynamic characteristics can be improved significantly., 資料番号: AA0004154000, レポート番号: NAL TM-670},
 title = {CAD設計によるUSB-STOL機半裁模型の風洞試験　第2報},
 year = {1994}
}