AN EXPERIMENT ON A CYLINDRICAL SCRAMJET COMBUSTOR (I) Simulated Flight Mach Number of 4.4

Material type: 文書・図像類

Author: 小室, 智幸ほか

Publisher: 航空宇宙技術研究所

Publication date: 1986-11

Material Format: Digital

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Note (General)：: An experimental study was made on a cylindrical scramjet combustor with a step using vitiated air. The stagnation temperature and the pressure of the ...

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Material Type: 文書・図像類
Title: AN EXPERIMENT ON A CYLINDRICAL SCRAMJET COMBUSTOR (I) Simulated Flight Mach Number of 4.4
Author/Editor: 小室, 智幸
村上, 淳郎
工藤, 賢司
升谷, 五郎
鎮西, 信夫
KOMURO, Tomoyuki
MURAKAMI, Atsuo
KUDO, Kenji
MASUYA, Goro
CHINZEI, NOBUO
Author Heading: 小室, 智幸
村上, 淳郎
工藤, 賢司
升谷, 五郎
鎮西, 信夫
KOMURO, Tomoyuki
MURAKAMI, Atsuo
KUDO, Kenji
MASUYA, Goro
CHINZEI, NOBUO
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1986-11
Publication Date (W3CDTF): 1986-11
Alternative Title: 円形断面スクラムジェット燃焼器の実験(Ⅰ)模擬飛行マッハ数4.4
Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-918
No. or year of volume/issue: 918
Volume: 918
Pages: 15-
ISSN (Periodical Title): ISSN : 0389-4010
Text Language Code: eng
Target Audience: 一般
Note (General): An experimental study was made on a cylindrical scramjet combustor with a step using vitiated air. The stagnation temperature and the pressure of the vitiated air were 1000 K and 1.5 MPa, respectively. Simulated flight speed was Mach 4.4 at a simulated altitude of 20 km. Perpendicular injection showed better mixing performance than did parallel injection. As equivalence ratio increased, supersonic combustion was switched to subsonic combustion. Mixing in the supersonic combustion mode was very slow compared with that in the subsonic mode.
資料番号: NALTR0918000
レポート番号: NAL TR-918
Access Restrictions: 限定公開
Data Provider (Database): 国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
https://irdb.nii.ac.jp
Original Data Provider (Database): 宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ