First Airframe Division, National Aerospace Laboratory(NAL)
First Airframe Division, National Aerospace Laboratory(NAL)
First Airframe Division, National Aerospace Laboratory(NAL)
First Airframe Division, National Aerospace Laboratory(NAL)
First Airframe Division, National Aerospace Laboratory(NAL)
First Airframe Division, National Aerospace Laboratory(NAL)
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-827
巻
827
ページ
11
発行年
1984-08
抄録（英）
The Effects of the fiber orientation on the transonic flutter characteristics of a sweptback wing with a core composite plate are examined experimentally. For this purpose, the two kinds of flutter model having the same planform but different bend-twist characteristics were made ; one has a wash-out tendency and the other a wash-in tendency. The wing has an aspect ratio of 5.0, a taper ratio of 0.50 and a leading edge sweep angle of 45 degrees. The airfoil section of this wing is a symmetrical NACA64A010. The flutter models were tested in the National Aerospace Laboratory’s 0.6m×0.6m blowdown wind tunnel. The flutter boundaries of both the wash-in and wash-out models were determined for a wide range of the transonic Mach numbers, namely, M∞=0.80～1.20. This experiment revealed that the wash-in model shows 25～30 percent higher flutter velocities than those of the wash-out model over the entire Mach number range tested.
複合材平板を芯材にした後退翼フラッタ模型の遷音速フラッタ試験(空力弾性テーラリング効果の検討)
naltr00827.pdf
(693.95KB)
