National Aerospace Laboratory Advanced Aircraft Research Group
National Aerospace Laboratory Advanced Aircraft Research Group
National Aerospace Laboratory Advanced Aircraft Research Group
National Aerospace Laboratory Advanced Aircraft Research Group
National Aerospace Laboratory Advanced Aircraft Research Group
出版者
航空宇宙技術研究所
出版者（英）
National Aerospace Laboratory (NAL)
雑誌名
航空宇宙技術研究所資料
雑誌名(英)
Technical Memorandum of National Aerospace Laboratory
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.
CAD設計によるUSB-STOL機半裁模型の風洞試験 第2報
naltm00670.pdf
(2.97MB)
