V/STOL Aircraft Research Group, National Aerospace Laboratory(NAL)
V/STOL Aircraft Research Group, National Aerospace Laboratory(NAL)
V/STOL Aircraft Research Group, National Aerospace Laboratory(NAL)
V/STOL Aircraft Research Group, National Aerospace Laboratory(NAL)
V/STOL Aircraft Research Group, National Aerospace Laboratory(NAL)
Mitsubishi Heavy Industries, Ltd.
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報告
雑誌名(英)
Technical Report of National Aerospace Laboratory TR-734
巻
734
ページ
32
発行年
1982-09
抄録（英）
An investigation has been conducted to determine the aerodynamic characteristics of the aerodynamic elements of an 8％ subsonic jet transport half model with an upper surface blowing flap system that would augment lift. Wind tunnel tests of leading edge and trailing edge high lift devices were conducted. After investigating those wind tunnel test data, some results were obtained. The set up angles of outer leading edge slats which were divided into three parts were all fixed at 40 degrees. It was determined that the USB flap was a hinged 40-70 type Forward-Main flap and that the inner leading edge had no device because any inner leading edge high lift devices were less effective in augmenting lift. Many data obtained in the wind tunnel tests were offered for the design of the NAL STOL Research Aircraft.
STOL実験機半截模型風洞試験(半截模型空力要素の特性)
naltr00734.pdf
(2.35MB)
