| 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 |
極超音速流れにおけるスティング干渉の実験 |
| 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 |
An Investigation of Support-Interference Effects in Hypersonic Flow |
| 著者 |
橋本, 登
穂積, 弘一
小山, 忠勇
吉沢, 昭
松崎, 貴至
HASHIMOTO, Noboru
HOZUMI, Koichi
KOYAMA, Tadao
YOSHIZAWA, Akira
MATSUZAKI, Takashi
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| 著者所属 |
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航空宇宙技術研究所空気力学第一部 |
| 著者所属 |
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航空宇宙技術研究所空気力学第一部 |
| 著者所属 |
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航空宇宙技術研究所空気力学第一部 |
| 著者所属 |
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航空宇宙技術研究所空気力学第一部 |
| 著者所属 |
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航空宇宙技術研究所空気力学第一部 |
| 著者所属（英） |
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en |
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First Aerodynamics Division, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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en |
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First Aerodynamics Division, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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en |
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First Aerodynamics Division, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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en |
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First Aerodynamics Division, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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en |
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First Aerodynamics Division, 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-622
巻 622,
p. 24,
発行日 1980-08
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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 |
Support-interference effects on hypersonic base pressure are investigated for various geometrical sting-support configurations in the NAL Hypersonic Wind Tunnel. Base pressure and pressure distribution on the sting surface in the flow having a free-stream Mach number of 7.1 and a free-stream Reynolds number based on the unit length from 0.2×10(exp 5) to 2.0×10(exp 5)/cm were measured. The oil flow observation on the sting surface was made at the same time. The angle of attack of the model is 0deg. The models are four spherically blunted cones with a semi-vertex angle of 10deg, a nose bluntness radii of 0.3, 3, 8 and 15 mm and a base diameter of 100mm. The support system consists of a strut, sting-pod and a sting. Three different stings having different lengths of 530, 252.5, and 127.5mm are used to examine the sting-flare effect on the base pressure. Avoiding the strong base pressure rise caused by the effect of strut, the sting-flare corner effect is investigtaed. The experimental results show that the base pressure depends upon the Reynolds number and is affected by the interaction of the base recirculating flow and the separated flow around the sting-flare corner. This effect of the sting-flare corner becomes smaller as the length of the sting increases and the standard length of a sting which has a sufficiently minimal effect on the base pressure is obtained. Above a Reynolds number of about 1.0×10(exp 5)/cm, the base recirculating flow and the separated flow over the flare are independent of each other and the base pressure changes discontinuously at a Reynolds number of about 1.0×10(exp 5)/cm in many cases. It seems to be caused by the transition of the boundary layer on the model surface. In order to predict the base pressure of the sting-mounted models, the correlation of the base pressure with local flow properties, immediately preceeding the base, is discussed for those cases where there is little effect from the sting-flare and strut. |
| 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: NALTR0622000 |
| 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-622 |
naltr00622.pdf (1.9 MB)
