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  1. F200 未来材料・システム研究所
  2. F200a 雑誌掲載論文
  3. 学術雑誌

Propulsion Performance of Cylindrical Rotating Detonation Engine

http://hdl.handle.net/2237/0002001417
http://hdl.handle.net/2237/0002001417
9b1adf8d-c930-41ef-ab94-c0df631751c0
名前 / ファイル ライセンス アクション
AIAA_Journal_cylindrical_RDE_yokoo.pdf AIAA_Journal_cylindrical_RDE_yokoo.pdf (1.7 MB)
Item type itemtype_ver1(1)
公開日 2021-09-09
タイトル
タイトル Propulsion Performance of Cylindrical Rotating Detonation Engine
言語 en
著者 Yokoo, Ryuya

× Yokoo, Ryuya

en Yokoo, Ryuya

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Goto, Keisuke

× Goto, Keisuke

en Goto, Keisuke

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Kim, Juhoe

× Kim, Juhoe

en Kim, Juhoe

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Kawasaki, Akira

× Kawasaki, Akira

en Kawasaki, Akira

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Matsuoka, Ken

× Matsuoka, Ken

en Matsuoka, Ken

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Kasahara, Jiro

× Kasahara, Jiro

en Kasahara, Jiro

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Matsuo, Akiko

× Matsuo, Akiko

en Matsuo, Akiko

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Funaki, Ikkoh

× Funaki, Ikkoh

en Funaki, Ikkoh

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アクセス権
アクセス権 open access
アクセス権URI http://purl.org/coar/access_right/c_abf2
内容記述
内容記述 This study evaluated the propulsion performance of a nozzleless, cylindrical rotating detonation engine (RDE). Using a C2H4–O2 mixture, the RDE was tested in a low-back-pressure environment at propellant mass flow rates of 8–45  g/s. In high-speed imaging of the self-luminescence within the combustor, rotating luminous regions were observed at mass flow rates above 22  g/s. Measured pressure distributions suggest that burned gas reached sonic velocity at the combustion chamber outlet. This paper proposes the structure of internal flow in the RDE and confirms that calculated pressure distribution based on the structure was close to the experimental distribution. This study also estimated the RDE’s thrust by pressure and momentum exchange and confirmed it by experimental measurement. Moreover, the theoretical thrust calculated under the assumption that exhaust is a sonic flow agreed with the load cell thrusts, suggesting that RDE combustion is perfectly completed inside the chamber. Specific impulses are 80–90% of specific impulses for ideal correct expanded flow for all mass flow rates, and its value was close to that of an annular RDE. In addition, RDE performance will increase by about 20% if the RDE is equipped with a divergent nozzle and the gas is correctly expanded to back pressure.
言語 en
内容記述タイプ Abstract
出版者
言語 en
出版者 American Institute of Aeronautics and Astronautics
言語
言語 eng
資源タイプ
資源タイプresource http://purl.org/coar/resource_type/c_6501
タイプ journal article
出版タイプ
出版タイプ AM
出版タイプResource http://purl.org/coar/version/c_ab4af688f83e57aa
関連情報
関連タイプ isVersionOf
識別子タイプ DOI
関連識別子 https://doi.org/10.2514/1.J058322
収録物識別子
収録物識別子タイプ PISSN
収録物識別子 0001-1452
書誌情報 en : AIAA Journal

巻 58, 号 12, p. 5107-5116, 発行日 2020-12
ファイル公開日
日付 2021-09-09
日付タイプ Available
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