Fundamental study of supersonic combustion in pure air flow with use of shock tunnel

Shigeru Aso; Arif Nur Hakim; Shingo Miyamoto; Kei Inoue; Yasuhiro Tani

Fundamental study of supersonic combustion in pure air flow with use of shock tunnel

Shigeru Aso, Arif Nur Hakim, Shingo Miyamoto, Kei Inoue, Yasuhiro Tani

宇宙システム工学

研究成果: 会議への寄与タイプ › 学会誌 › 査読

抄録

An experimental study using reflected type of shock tunnel has been conducted to investigate the phenomena of supersonic combustion. In the experiment, test air is compressed by reflected shock wave up to stagnation temperature of 2800 K and stagnation pressure of 0.35 MPa. Heated air is used as a reservoir gas of supersonic nozzle. Hydrogen is injected transversely through circular hole into freestream of Mach 2. Flow duration is 300 microseconds. Schlieren method and CCD UV camera is used to obtain information on the shock structures and the region of combustion. The effects of total pressure of injection gas to the fuel penetration and the region of combustion have been revealed.

本文言語	英語
ページ	7166-7171
ページ数	6
出版ステータス	出版済み - 2004
イベント	International Astronautical Federation - 55th International Astronautical Congress 2004 - Vancouver, カナダ継続期間: 10月 4 2004 → 10月 8 2004

その他

その他	International Astronautical Federation - 55th International Astronautical Congress 2004
国/地域	カナダ
City	Vancouver
Period	10/4/04 → 10/8/04

!!!All Science Journal Classification (ASJC) codes

航空宇宙工学
宇宙惑星科学

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引用スタイル

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author = "Shigeru Aso and Hakim, {Arif Nur} and Shingo Miyamoto and Kei Inoue and Yasuhiro Tani",

year = "2004",

language = "English",

pages = "7166--7171",

note = "International Astronautical Federation - 55th International Astronautical Congress 2004 ; Conference date: 04-10-2004 Through 08-10-2004",

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T1 - Fundamental study of supersonic combustion in pure air flow with use of shock tunnel

AU - Aso, Shigeru

AU - Hakim, Arif Nur

AU - Miyamoto, Shingo

AU - Inoue, Kei

AU - Tani, Yasuhiro

PY - 2004

Y1 - 2004

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AB - An experimental study using reflected type of shock tunnel has been conducted to investigate the phenomena of supersonic combustion. In the experiment, test air is compressed by reflected shock wave up to stagnation temperature of 2800 K and stagnation pressure of 0.35 MPa. Heated air is used as a reservoir gas of supersonic nozzle. Hydrogen is injected transversely through circular hole into freestream of Mach 2. Flow duration is 300 microseconds. Schlieren method and CCD UV camera is used to obtain information on the shock structures and the region of combustion. The effects of total pressure of injection gas to the fuel penetration and the region of combustion have been revealed.

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T2 - International Astronautical Federation - 55th International Astronautical Congress 2004

Y2 - 4 October 2004 through 8 October 2004

ER -

Fundamental study of supersonic combustion in pure air flow with use of shock tunnel

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その他

!!!All Science Journal Classification (ASJC) codes

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