@techreport{oai:jaxa.repo.nii.ac.jp:00045114,
 author = {安藤, 泰勝 and 松崎, 雄嗣 and 江尻, 宏 and 菊池, 孝男 and ANDO, Yasukatsu and MATSUZAKI, Yuji and EJIRI, Hiroshi and KIKUCHI, Takao},
 month = {Apr},
 note = {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., 資料番号: NALTR0856000, レポート番号: NAL TR-856},
 title = {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},
 year = {1985}
}