| 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 |
二次噴射を伴う超音速円錐ノズル内の流れ |
| 言語 |
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言語 |
jpn |
| 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（英） |
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その他のタイトル |
Flowfield Induced by a Secondary Jet in a Supersonic Conical Nozzle |
| 著者 |
升谷, 五郎
鎮西, 信夫
石井, 進一
村上, 淳郎
小室, 智幸
MASUYA, Goro
CHINZEI, NOBUO
ISHII, Shinichi
MURAKAMI, Atsuo
KOMURO, Tomoyuki
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| 著者所属 |
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角田支所 |
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角田支所 |
| 著者所属 |
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角田支所 |
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角田支所 |
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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) |
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en |
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Kakuda Branch Office, National Aerospace Laboratory(NAL) |
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en |
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Kakuda Branch Office, National Aerospace Laboratory(NAL) |
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en |
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Kakuda Branch Office, National Aerospace Laboratory(NAL) |
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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-479
巻 479,
p. 16,
発行日 1976-12
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| 抄録（英） |
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内容記述タイプ |
Other |
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内容記述 |
The flowfield induced by secondary gas injection into a supersonic conical nozzle with a 9.6 deg half-angle was investigated experimentally. Mach number and Reynolds number of the main stream at the injection point, without injection, were 2.1 and 7.0×10(exp 6), respectively. Flow direction, Pitot pressure and cone surface pressure over a cross section, and nozzle wall static pressure were measured with the main point of interest being the downstream part of the injection port. Static pressure and Mach number distributions over a cross section were deduced from the Pitot and cone surface pressures. These distributions suggest that the flow downstream of the injection port is composed of three shock waves and five regions. Axial development of the flowfield and the effect of the stagnation pressure ratio of the secondary jet to the main stream on the flow structure were also investigated. Axial variations in the maximum value of the wall static pressure in cross sections were compared with the calculated pressure ratios behind the bow shock and its reflected wave. In addition, axially unsymmetric separation lines caused by secondary injection into an overexpanded nozzle flow are shown along with wall static pressure data. |
| 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: NALTR0479000 |
| レポート番号 |
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内容記述タイプ |
Other |
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内容記述 |
レポート番号: NAL TR-479 |
naltr00479.pdf (2.0 MB)
