| Item type |
テクニカルレポート / Technical Report(1) |
| 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内部流れの解析 |
| 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 |
Numerical Analysis of Flow in a Scramjet Engine |
| 著者 |
佐藤, 哲也
梶, 昭次郎
Sato, Tetsuya
Kaji, Shojiro
|
| 著者所属 |
|
|
|
東京大学大学院 |
| 著者所属 |
|
|
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東京大学工学部航空学科 |
| 著者所属（英） |
|
|
|
en |
|
|
Graduate School, University of Tokyo |
| 著者所属（英） |
|
|
|
en |
|
|
Department of Aeronautics, University of Tokyo |
| 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-10
巻 10,
p. 93-98,
発行日 1989-11
|
| 抄録（英） |
|
|
内容記述タイプ |
Other |
|
内容記述 |
In the airframe-integrated scramjet engines, the inlet flow is accompanied by a strong gradient of Mach number as well as mass flux owing to the forebody thick boundary layer which cannot be diverted outside engines because of its high temperature. If such engines are designed for uniform inlet flows they cannot endure this type of inlet flow gradient, and a strong pressure loss occurs at the inlet. In this study the flow mechanics of scramjet engines subject to a forebody boundary layer are investigated, and various phenomena such as compound choking and the transition of inlets from start to unstart conditions are revealed. First, the influence of boundary layers is studied by a combined one-dimensional stream tube model. Then the flow field of an engine is analyzed using a quasi-three-dimensional finite difference model. The explicit MacCormack method is used. It is shown that a scramjet engine designed for a uniform inlet flow experiences choking by the presence of a low-speed region like a boundary layer. This phenomenon is called compound choking. When a compound choking occurs, it is shown that the throat Mach number is not unity but that in the boundary layer the flow is subsonic while it is supersonic in the main strream region. The processes of transition of an inlet from start to unstart conditions are shown to depend remarkably on width and shear strength of the boundary layer. It is also shown that an engine with a sweep angle is very tolerant of such flow non-uniformities. |
| 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 |
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|
内容記述タイプ |
Other |
|
内容記述 |
資料番号: NALSP0010016 |
| 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-10 |
nalsp0010016.pdf (337.4 kB)
