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Computation of Two-Dimensional, Transonic, Chemically Reacting Nonequilibrium Flow in a Rocket Nozzle
https://jaxa.repo.nii.ac.jp/records/31171
https://jaxa.repo.nii.ac.jp/records/311710d21038a-bf5b-4013-82af-708da5a33913
| 名前 / ファイル | ライセンス | アクション |
|---|---|---|
SA0033404.pdf (756.7 kB)
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| Item type | 紀要論文 / Departmental Bulletin Paper(1) | |||||||
|---|---|---|---|---|---|---|---|---|
| 公開日 | 2015-03-26 | |||||||
| タイトル | ||||||||
| タイトル | Computation of Two-Dimensional, Transonic, Chemically Reacting Nonequilibrium Flow in a Rocket Nozzle | |||||||
| 言語 | en | |||||||
| 言語 | ||||||||
| 言語 | eng | |||||||
| 資源タイプ | ||||||||
| 資源タイプ識別子 | http://purl.org/coar/resource_type/c_6501 | |||||||
| 資源タイプ | departmental bulletin paper | |||||||
| 著者 |
NAKAHASHI, Kazuhiro
× NAKAHASHI, Kazuhiro
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| 著者所属（英） | ||||||||
| en | ||||||||
| National Aerospace Laboratory | ||||||||
| 出版者 | ||||||||
| 出版者 | 宇宙科学研究所 | |||||||
| 出版者（英） | ||||||||
| 出版者 | Institute of Space and Astronautical Science | |||||||
| 書誌情報 |
en : The Institute of Space and Astronautical Science report. S.P. : Proceedings of the Symposium on Mechanics for Space Flight 巻 1, p. 51-64, 発行日 1983-03 |
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| 抄録（英） | ||||||||
| 内容記述タイプ | Other | |||||||
| 内容記述 | A time-dependent, semi-implicit scheme is developed for solving the equations governing two-dimensional, chemically reacting nonequilibrium flow inside rocket nozzles. Subsonic and transonic flowfields of the nozzle entrance and throat region can be analyzed using this computational scheme. All equations of motion are solved simultaneously at each grid point by treating the time derivatives implicitly, in order to make the scheme stable with respect to the chemical rates. By evaluating spatial derivative terms explicitly, the scheme is made simple and has the advantage that only a relatively small computer storage is required. Results are presented at first for a nonreacting flow inside the JPL nozzle in order to illustrate the proposed scheme's validity by comparing with the experimental data and the result of the Cline's scheme. Then the nozzle flowfield of a hydrogen-oxygen rocket engine is analyzed. A computational result of C-H-O-N system (nitrogen tetroxide and a blend of 50 percent hydrazine and 50 percent unsymmetrical dimethylhydrazine) is also presented. | |||||||
| ISSN | ||||||||
| 収録物識別子タイプ | ISSN | |||||||
| 収録物識別子 | 0288-433X | |||||||
| 書誌レコードID | ||||||||
| 収録物識別子タイプ | NCID | |||||||
| 収録物識別子 | AA10455137 | |||||||
| 資料番号 | ||||||||
| 内容記述タイプ | Other | |||||||
| 内容記述 | 資料番号: SA0033404000 | |||||||
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Cite as
NAKAHASHI, Kazuhiro, 1983, Computation of Two-Dimensional, Transonic, Chemically Reacting Nonequilibrium Flow in a Rocket Nozzle: 宇宙科学研究所, 51–64 p.
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