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RJTF Mach 8 tests of a scramjet engine with strut and ramp compression
https://jaxa.repo.nii.ac.jp/records/42984
https://jaxa.repo.nii.ac.jp/records/4298493a123a0-d93c-45f0-bfbe-de55d71fe15d
名前 / ファイル | ライセンス | アクション |
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naltr0001471t.pdf (1.1 MB)
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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 | ||||||
言語 | en | |||||
タイトル | RJTF Mach 8 tests of a scramjet engine with strut and ramp compression | |||||
言語 | ||||||
言語 | eng | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | スクラムジェットエンジン | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | マッハ数 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | エンジン試験 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | ストラット・ランプ圧縮 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 燃焼効率 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | RJTF | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 研究施設 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 高温 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | scramjet engine | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Mach number | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | engine test | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | strut-ramp compression | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | combustion efficiency | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | RJTF | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | research facility | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | high temperature | |||||
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 | ||||||
その他のタイトル | ストラット・ランプ圧縮を伴うスクラムジェットエンジンのRJTFマッハ8試験 | |||||
著者 |
苅田, 丈士
× 苅田, 丈士× 三谷, 徹× 志村, 隆× 佐藤, 茂× 工藤, 賢司× Kanda, Takeshi× Mitani, Toru× Shimura, Takashi× Sato, Shigeru× Kudo, Kenji |
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著者所属 | ||||||
航空宇宙技術研究所 角田宇宙推進技術研究所 | ||||||
著者所属 | ||||||
航空宇宙技術研究所 角田宇宙推進技術研究所 | ||||||
著者所属 | ||||||
航空宇宙技術研究所 角田宇宙推進技術研究所 | ||||||
著者所属 | ||||||
航空宇宙技術研究所 角田宇宙推進技術研究所 | ||||||
著者所属 | ||||||
航空宇宙技術研究所 角田宇宙推進技術研究所 | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory Kakuda Space Propulsion Laboratory | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory Kakuda Space Propulsion Laboratory | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory Kakuda Space Propulsion Laboratory | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory Kakuda Space Propulsion Laboratory | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory Kakuda Space Propulsion 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報告 en : Technical Report of National Aerospace Laboratory 巻 1471T, 発行日 2003-08 |
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抄録 | ||||||
内容記述タイプ | Abstract | |||||
内容記述 | ラムジェットエンジン試験設備(RJTF)におけるマッハ8条件での始動性および燃焼性能を改善するために、ストラットに加えてランプを取り付けたスクラムジェットエンジン模型の試験を行った。燃料を垂直噴射した時に、エンジン出口での燃焼効率は約90%であった。当量比1.3の条件時に、590Nの推力増加を測定した。しかしながら最適化されていないエンジン形状であったために、十分な推力増加は得られなかった。着火および燃焼に必要な高い温度および圧力が、ランプの装着によって達成された。燃焼器内圧が、エンジンに流入する気流圧力の160倍に達した場合にも、インレットは始動状態を保つことができた。これはランプを用いてインレット内圧力を上昇させた効果による。 | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | To improve combustion efficiency and the inlet start condition, a scramjet model with a ramp combined with a single strut was tested under Mach 8 flight conditions at the Ramjet Engine Test Facility of the Ramjet Propulsion Research Center. The attached ramp shielded some of the fuel injectors. The fuel flow rate from the open injectors to the flow path was designated as the effective fuel flow rate. In the tests, a combustion efficiency of 90 percent was attained with vertical injection of hydrogen fuel. The thrust increase was 590 N at the effective equivalence ratio of 1.3. However, because the engine geometry was not optimized, a sufficient increase in thrust was not attained. The high temperature and high pressure necessary for ignition and combustion were achieved by the ramp. When the pressure in the isolator was 160 times that of the free-stream air due to combustion, the inlet was in the started condition despite the high pressure. This improved started condition was attained by using the ramp to increase the pressure in the inlet. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 1347-4588 | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AN00311347 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0047391000 | |||||
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 TR-1471T |