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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
https://jaxa.repo.nii.ac.jp/records/45114
https://jaxa.repo.nii.ac.jp/records/451143f2b6052-cc2e-45a9-ac1b-bdc4b778487d
名前 / ファイル | ライセンス | アクション |
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naltr00856.pdf (1.4 MB)
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Item type | テクニカルレポート / Technical Report(1) | |||||
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公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | 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 | |||||
言語 | ||||||
言語 | jpn | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_18gh | |||||
資源タイプ | technical report | |||||
その他のタイトル(英) | ||||||
その他のタイトル | Estimation of Divergence and Flutter Boundaries on Supersonic Plate Wing Models from Subcritical Random Responses due to Air Turbulence | |||||
著者 |
安藤, 泰勝
× 安藤, 泰勝× 松崎, 雄嗣× 江尻, 宏× 菊池, 孝男× ANDO, Yasukatsu× MATSUZAKI, Yuji× EJIRI, Hiroshi× KIKUCHI, Takao |
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著者所属 | ||||||
航空宇宙技術研究所機体第一部 | ||||||
著者所属 | ||||||
元・航空宇宙技術研究所機体第一部 | ||||||
著者所属 | ||||||
航空宇宙技術研究所機体第一部 | ||||||
著者所属 | ||||||
航空宇宙技術研究所機体第一部 | ||||||
著者所属(英) | ||||||
en | ||||||
First Airframe Division, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
Former First Airframe Division, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
First Airframe Division, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
First Airframe Division, National Aerospace Laboratory(NAL) | ||||||
出版者 | ||||||
出版者 | 航空宇宙技術研究所 | |||||
出版者(英) | ||||||
出版者 | National Aerospace Laboratory(NAL) | |||||
書誌情報 |
航空宇宙技術研究所報告 en : Technical Report of National Aerospace Laboratory TR-856 巻 856, p. 16, 発行日 1985-04 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | 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. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 0389-4010 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: NALTR0856000 | |||||
レポート番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | レポート番号: NAL TR-856 |