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スクラムジェットエンジンの流れの3次元Navier-Stokes解析(ストラット付空気取入口)
https://jaxa.repo.nii.ac.jp/records/43521
https://jaxa.repo.nii.ac.jp/records/4352196ec3375-7dd8-4998-9e45-a51a330ff79f
名前 / ファイル | ライセンス | アクション |
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nalsp0016025.pdf (426.7 kB)
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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 | スクラムジェットエンジンの流れの3次元Navier-Stokes解析(ストラット付空気取入口) | |||||
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 | 3D Navier-Stokes Calculation of Flow about Scramjet Inlet with Strut | |||||
著者 |
石黒, 登美子
× 石黒, 登美子× 末松, 和代× 和田, 安弘× 小川, 哲× Ishiguro, Tomiko× Suematu, Kazuyo× Wada, Yusuhiro× Ogawa, Satoru |
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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 | ||||||
航空宇宙技術研究所 | ||||||
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 | ||||||
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 SP-16 巻 16, p. 159-164, 発行日 1991-12 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | A numerical procedure to analyze a flowfield through or around a Langley-typed scramjet engine inlet with a strut and an I-shaped thick cowl is proposed. To treat boundary conditions (wall, symmetry etc.) accurately, all boundaries are mapped onto faces of five rectangular parallelepipeds. The governing equations are the 3D full Navier-Stokes equations. The TVD scheme is applied for spatial discretizations and the IAF method, for time integration. To show capability of the numerical procedure, numerical simulations of flow have been carried out under Mach number 4 of free stream about four inlet models, whose struts differ in lengths but have the same contraction ratios. The result has made no great difference from each other in inlet performance such as mass capture ratio and total pressure recovery ratio. | |||||
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: NALSP0016025 | |||||
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-16 |