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

doi:10.1016/j.actaastro.2005.03.055

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: ジャーナルへの寄稿 › 会議記事 › 査読

28 被引用数 (Scopus)

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 μs. Schlieren method and CCD UV camera are 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 obtained.

本文言語	英語
ページ（範囲）	384-389
ページ数	6
ジャーナル	Acta Astronautica
巻	57
号	2-8
DOI	https://doi.org/10.1016/j.actaastro.2005.03.055
出版ステータス	出版済み - 7月 1 2005
イベント	Infinite Possibilities Global Realities, Selectred Proceedings of the 55th International Astronautical Federation Congress, Vancouver - 継続期間: 10月 4 2004 → 10月 8 2004

!!!All Science Journal Classification (ASJC) codes

航空宇宙工学

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10.1016/j.actaastro.2005.03.055

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引用スタイル

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abstract = "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 μs. Schlieren method and CCD UV camera are 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 obtained.",

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AU - Aso, Shigeru

AU - Hakim, Arif Nur

AU - Miyamoto, Shingo

AU - Inoue, Kei

AU - Tani, Yasuhiro

PY - 2005/7/1

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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 μs. Schlieren method and CCD UV camera are 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 obtained.

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JO - Acta Astronautica

JF - Acta Astronautica

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T2 - Infinite Possibilities Global Realities, Selectred Proceedings of the 55th International Astronautical Federation Congress, Vancouver

Y2 - 4 October 2004 through 8 October 2004

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

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!!!All Science Journal Classification (ASJC) codes

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