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Warped Delta翼における超音速層流制御効果に関する考察
https://jaxa.repo.nii.ac.jp/records/37354
https://jaxa.repo.nii.ac.jp/records/373547325ad63-fa89-43aa-a063-969c4f4acabb
名前 / ファイル | ライセンス | アクション |
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nalsp0041040.pdf (621.6 kB)
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Item type | 会議発表論文 / Conference Paper(1) | |||||
---|---|---|---|---|---|---|
公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | Warped Delta翼における超音速層流制御効果に関する考察 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | warped delta翼 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 層流制御 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 摩擦抗力 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 揚抗比 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 流れの可視化 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 遷移位置 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | CFD解析 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 層流境界層 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 安定解析 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 圧力分布 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 吸い込み | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 数値流体力学 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 超音速層流流れ | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | warped delta wing | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | laminar flow control | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | friction drag | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | lift to drag ratio | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | flow visualization | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | transition location | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | CFD analysis | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | laminar boundary layer | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | stability analysis | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | pressure distribution | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | suction | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | computational fluid dynamics | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | supersonic laminar flow | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_5794 | |||||
資源タイプ | conference paper | |||||
その他のタイトル(英) | ||||||
その他のタイトル | Study on supersonic laminar flow control on a warped delta wing | |||||
著者 |
生越, 博景
× 生越, 博景× 稲垣, 健次郎× 石田, 洋治× 吉田, 憲司× 野口, 正芳× Ogoshi, Hirokage× Inagaki, Kenjiro× Ishida, Yoji× Yoshida, Kenji× Noguchi, Masayoshi |
|||||
著者所属 | ||||||
川崎重工業 | ||||||
著者所属 | ||||||
川崎重工業 | ||||||
著者所属 | ||||||
航空宇宙技術研究所 | ||||||
著者所属 | ||||||
航空宇宙技術研究所 | ||||||
著者所属 | ||||||
航空宇宙技術研究所 | ||||||
著者所属(英) | ||||||
en | ||||||
Kawasaki Heavy Industries Ltd | ||||||
著者所属(英) | ||||||
en | ||||||
Kawasaki Heavy Industries Ltd | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory | ||||||
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特別資料 en : Special Publication of National Aerospace Laboratory 巻 41, p. 259-264, 発行日 1999-02 |
|||||
会議概要(会議名, 開催地, 会期, 主催者等) | ||||||
内容記述タイプ | Other | |||||
内容記述 | 航空宇宙技術研究所 24-26 Jun. 1998 東京 日本 | |||||
会議概要(会議名, 開催地, 会期, 主催者等)(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | National Aerospace Laboratory 24-26 Jun. 1998 Tokyo Japan | |||||
抄録 | ||||||
内容記述タイプ | Abstract | |||||
内容記述 | 超音速輸送機(SST)の揚抗比改善のためには摩擦抗力を低減する必要があるので、実際の空気動力学的設計への応用の観点から、Warp形状翼に関する超音速層流制御効果について検討してきた。今回、実験によりマッハ数M=1.4における吸い込みに起因する大幅な低減を実験的に確認し、また層流境界層の安定性を数値計算的に解析した。 | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Since the friction drag of an SST (Supersonic Transport) must be reduced to improve the lift-to-drag ratio, supersonic laminar flow control on a warped wing has been investigated from a viewpoint of applying it to real aerodynamic design. Then large reduction due to suction at M = 1.4 was experimentally confirmed and the stability of laminar boundary layer was numerically analyzed. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 0289-260X | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AN10097345 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0001958040 | |||||
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 SP-41 |