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固体壁近傍における密度勾配と衝撃波との干渉
https://jaxa.repo.nii.ac.jp/records/38079
https://jaxa.repo.nii.ac.jp/records/380792aeab33d-fbe3-4d91-b27a-7fad36b97f1a
名前 / ファイル | ライセンス | アクション |
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nalsp0053042.pdf (1.3 MB)
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Item type | 会議発表論文 / Conference Paper(1) | |||||
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公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | 固体壁近傍における密度勾配と衝撃波との干渉 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 衝撃波相互作用 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 密度勾配 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 空気力学力 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 超音速燃焼ラムジェット・エンジン | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 数値解析 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | Navier-Stokes方程式 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 有限差分論 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | shock wave interaction | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | density gradient | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | aerodynamic force | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | supersonic combustion ramjet engine | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | numerical analysis | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Navier-Stokes equation | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | finite difference theory | |||||
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 | Shock wave interaction with density gradient near solid wall | |||||
著者 |
小幡, 茂男
× 小幡, 茂男× Obata, Shigeo |
|||||
著者所属 | ||||||
防衛大学校 | ||||||
著者所属(英) | ||||||
en | ||||||
National Defense Academy | ||||||
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: 航空宇宙数値シミュレーション技術シンポジウム2001論文集 en : Special Publication of National Aerospace Laboratory: Proceedings of Aerospace Numerical Simulation Symposium 2001 巻 53, p. 251-256, 発行日 2002-01 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | The baroclinic torque, an aerodynamical force induced by special misalignment between density gradient of mixing layer and pressure gradient of shock wave, is able to achieve fine mixing enhancement characteristics in fuel gas injection for supersonic combustion of SCRAM jet engine. The effect of reciprocal passage of a normal shock wave, forward and backward propagation through a 2-D circular shape helium gas surrounded by air, on mixing process is numerically analyzed. A governing equation system including Navier-Stokes and species mass conservation equation is solved by TVD formulated finite differential method. After the primary interaction of forward propagating normal shock wave, M(sub s) = 1.5, the helium gas is divided to two elliptic parts. Each part shows a symmetrical vortical motion. Similarly the secondary reflection wave cuts off each part to tiny twins with contra-vorticities. Though a reciprocal motion of shock wave produces contra-direction of baroclinic torque on helium gas, the combination never contribute to suppress mixing but accelerate homogeneity of concentration between helium and air. | |||||
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: AA0032819043 | |||||
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-53 |