First Airframe Division, National Aerospace Laboratory(NAL)
First Airframe Division, National Aerospace Laboratory(NAL)
Former First Airframe Division, National Aerospace Laboratory(NAL)
First Airframe Division, National Aerospace Laboratory(NAL)
Former 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-314
An experimental investigation of some effects of varied location of added mass at wing tip on transonic flutter characteristics of thin cantilever wings has been conducted in the N.A.L. 60cm×60cm transonic blowdown wind tunnel for flutter testing at Mach number between 0.819 and 1.192. The wings have sweptback angle of 42.5 deg at leading edge and of 10 deg at trailing edge, panel aspect ratio of 1.344 and taper ratio of 0.336. The flutter boundary expressed by the experimental flutter-velocity coefficient is characterized by having maximum values at around Mach number 1.03, and stable region expands by moving forword C.G. location of the added mass.
低アスペクト比後退角平板翼の遷音速フラッタ特性におよぼす翼端付加質量の重心位置の影響
naltr00314.pdf
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