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Aeroelastic simulation for SST configuration
https://jaxa.repo.nii.ac.jp/records/37320
https://jaxa.repo.nii.ac.jp/records/37320972bef38-df3d-4969-abf7-3297825f0e04
Item type | 会議発表論文 / Conference Paper(1) | |||||
---|---|---|---|---|---|---|
公開日 | 2015-03-26 | |||||
タイトル | ||||||
言語 | en | |||||
タイトル | Aeroelastic simulation for SST configuration | |||||
言語 | ||||||
言語 | eng | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | SST | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | フラップ強制振動 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 空力弾性応答 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 数値シミュレーション | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 薄層ナビエ・ストークス方程式 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 超音速輸送機 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 遷音速風洞 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | CFD | |||||
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 | TVD | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 全変動減少 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | ADI形式 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | alternating direction implicit形式 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | SST | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | forced flap oscillation | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | aeroelastic response | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | numerical simulation | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | thin layer Navier Stokes equation | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | supersonic transport | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | transonic wind tunnel | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | CFD | |||||
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 | TVD | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | total variation diminishing | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | ADI form | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | alternating direction implicit form | |||||
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 | |||||
アクセス権 | ||||||
アクセス権 | metadata only access | |||||
アクセス権URI | http://purl.org/coar/access_right/c_14cb | |||||
その他のタイトル | ||||||
その他のタイトル | SST形態の空力弾性数値シミュレーション | |||||
著者 |
Kheirandish, Hamid Reza
× Kheirandish, Hamid Reza× 中道, 二郎× Kheirandish, Hamid Reza× Nakamichi, Jiro |
|||||
著者所属 | ||||||
計算力学研究センター | ||||||
著者所属 | ||||||
航空宇宙技術研究所 | ||||||
著者所属(英) | ||||||
en | ||||||
Research Center of Computational Mechanics Inc | ||||||
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. 41-46, 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 | SST(超音速輸送機)型矢状翼のフラップの強制振動に対する空力弾性応答の数値シミュレーションを行った。薄層ナビエ・ストークス方程式に基づく数値計算コードを開発した。本コードはHartenのTVD(全変動減少)型スキームのADI(Alternating Direction Implicit)形式を支配方程式の積分に用いた。フラップの振動数と全圧力15Hz、30Hzおよび80kPa、120kPaにおける翼の応答を求め測定データと比較した。NALの2×2m遷音速風洞を用いて固定および振動フラップの定常、非定状態について実験的なテストを行った。 | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | The numerical simulation of aeroelastic response of a SST (Supersonic Transport) type arrow wing flutter model to the forced oscillation of flap is presented. A numerical code based on the thin layer Navier-Stokes equations has been developed. The code uses ADI (Alternating Direction Implicit) form of Harten's TVD (Total Variation Diminishing) type scheme to integrate the governing equations. The wing responses to flap oscillation frequencies and total pressures of 15 Hz, 30 Hz and 80 kPa, 120 kPa were obtained and compared to the experimental ones. The experimental tests have been done for steady and unsteady cases with fixed or oscillating flap at NAL 2 x 2 m transonic wind tunnel. | |||||
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: AA0001958006 | |||||
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 |