| Item type |
テクニカルレポート / Technical Report(1) |
| 公開日 |
2015-03-26 |
| タイトル |
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タイトル |
Experiment on a Cylindrical Scramjet Combustor (II) Simulated Flight Mach Number 6.7 |
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言語 |
en |
| 言語 |
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言語 |
eng |
| 資源タイプ |
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資源タイプ識別子 |
http://purl.org/coar/resource_type/c_18gh |
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資源タイプ |
technical report |
| その他のタイトル |
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その他のタイトル |
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 |
| 著者 |
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
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| 著者所属 |
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航空宇宙技術研究所角田支所 |
| 著者所属 |
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航空宇宙技術研究所角田支所 |
| 著者所属 |
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航空宇宙技術研究所角田支所 |
| 著者所属 |
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航空宇宙技術研究所角田支所 |
| 著者所属 |
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航空宇宙技術研究所角田支所 |
| 著者所属（英） |
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en |
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Kakuda Branch Office, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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en |
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Kakuda Branch Office, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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en |
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Kakuda Branch Office, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
|
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|
en |
|
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Kakuda Branch Office, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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|
en |
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Kakuda Branch Office, National Aerospace Laboratory(NAL) |
| 出版者 |
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出版者 |
航空宇宙技術研究所 |
| 出版者（英） |
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出版者 |
National Aerospace Laboratory(NAL) |
| 書誌情報 |
航空宇宙技術研究所報告
en : Technical Report of National Aerospace Laboratory TR-969
巻 969,
p. 18,
発行日 1988-03
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| 抄録（英） |
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内容記述タイプ |
Other |
|
内容記述 |
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. |
| ISSN |
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収録物識別子タイプ |
ISSN |
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収録物識別子 |
0389-4010 |
| 資料番号 |
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内容記述タイプ |
Other |
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内容記述 |
資料番号: NALTR0969000 |
| レポート番号 |
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内容記述タイプ |
Other |
|
内容記述 |
レポート番号: NAL TR-969 |
naltr00969.pdf (1.2 MB)
