First Airframe Division, National Aerospace Laboratory(NAL)
Former 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-856
巻
856
ページ
16
発行年
1985-04
抄録（英）
The National Aerospace Laboratory (NAL) method was applied to the response data which were obtained from subcritical flutter and divergence tests conducted in the NAL supersonic wind tunnel. Backward- and forward-swept wing models were used for the flutter and divergence tests, respectively. The stationary sampled time responses were modeled by both the autoregressive moving average (ARMA) and autoregressive (AR) processes. It has been shown that both flutter and divergence boundaries in a supersonic flow range can well be estimated as those in the transonic flow region.
気流の乱れを利用した超音速平板翼模型のダイバージエンスとフラッタ限界の推定
naltr00856.pdf
(1.36MB)
