Experiment on a Cylindrical Scramjet Combustor (II) Simulated Flight Mach Number 6.7

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: 1988-03

Material Format: Digital

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Note (General)：: An experimental study was made on a cylindrical scramjet combustor with a rearfacing step in a vitiated air flow. The stagnation temperature and press...

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Material Type: 文書・図像類
Title: Experiment on a Cylindrical Scramjet Combustor (II) Simulated Flight Mach Number 6.7
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: 1988-03
Publication Date (W3CDTF): 1988-03
Alternative Title: 円形断面スクラムジェット燃焼器の実験(Ⅱ)模擬飛行マッハ数6.7
Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-969
No. or year of volume/issue: 969
Volume: 969
Pages: 18-
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 rearfacing step in a vitiated air flow. The stagnation temperature and pressure of the vitiated air were 2000 K and 1.0 MPa, respectively. The simulated flight speed was Mach 6.7 at a particular altitude of 40 km. Three different types of fuel injector were used, consiting of two perpendicular schemes and a parallel scheme of fuel injection into the mainstream. Auto-ignition of hydrogen fuel occurred when the air stagnation temperature reached about 1500K. In all test cases, the flame was anchored on the step. For high air stagnation temperature and low fuel flow rate, however, the flame holding position shifted downstream from the step. At a fuel equivalence ratio of 0.55, mixing efficiency of the parallel injector was higher than that of the perpendicular injectors, but the axial variations in combustion efficiency were almost in the same form for all injectors, except immediately downstream of the injector. In a supersonic combustion mode, significant influence of flight Mach number on mixing was not observed. For a constant inlet Mach number, fuel flow rates at which transition from supersonic to subsonic combustion took place increased nearly in proportion to the stagnation temperature of air. A one-dimensional analysis using the measured pressure distribution served to determine other chemical and fluid mechanical properties. The calculated combustion efficiencies were slightly higher as compared to the experimental data, while the Mach number distributions were in reasonable agreement.
資料番号: NALTR0969000
レポート番号: NAL TR-969
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