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65207039.pdf1.34 MB
title超音速インテーク周りの衝撃波振動現象に関する研究
Other TitleStudy of the Shock Oscillationin Supersonic Inlets
Author(jpn)中山, 智裕; 佐藤, 哲也; 橋本, 敦; 小島, 孝之; 田口, 秀之
Author(eng)Nakayama, Tomohiro; Sato, Tetsuya; Hashimoto, Atsushi; Kojima, Takayuki; Taguchi, Hideyuki
Author Affiliation(jpn)早稲田大学; 早稲田大学; 宇宙航空研究開発機構 (JAXA); 宇宙航空研究開発機構 (JAXA); 宇宙航空研究開発機構 (JAXA)
Author Affiliation(eng)Waseda University; Waseda University; Japan Aerospace Exploration Agency (JAXA); Japan Aerospace Exploration Agency (JAXA); Japan Aerospace Exploration Agency (JAXA)
Issue Date2012-03-30
Publisher宇宙航空研究開発機構
Japan Aerospace Exploration Agency (JAXA)
Publication title宇宙航空研究開発機構特別資料: 第43回流体力学講演会: 航空宇宙数値シミュレーション技術シンポジウム2011論文集
JAXA special publication: Proceedings of 43rd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2011
VolumeJAXA-SP-11-015
Start page225
End page230
Publication date2012-03-30
Languagejpn
eng
AbstractInlet buzz, a shock oscillation phenomenon in supersonic air inlets was studied both numerically and experimentally. Following a supersonic wind tunnel test, a computation alanalysis was implemented on the supersonic air inlet of the "S-engine" which is a sub-scaled pre-cooled turbo jet engine. The experiment was performed at JAXA's Sagamihara campus. The free stream Mach number was 2.0 and the Reynolds number was 9.193 × 10(exp 5). Shock oscillation, known as "Dailey type inlet buzz", was observed when the outlet nozzle area gradually reduced from its initial full throttling and the mass-flow was limited. The numerical simulation was conducted under the condition of the outlet nozzle contraction ratio Ae/At (exit area/inlet throat area)=0.7. The CFD analysis showed a good agreement with the experiment. It was indicated that a flow field with subcritical shock configuration and supercritical mass capture characteristics appeared when the free stream Mach number was significantly lower than the inlet's design point. It was also observed that the inlet buzz was not triggered when the volume of the aft duct was smaller than a certain value.
DescriptionPhysical characteristics: Original contains color illustrations
Meeting Information: 43rd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2011 (July 7-8, 2011. Waseda University, International Conference Center), Tokyo Japan
形態: カラー図版あり
会議情報: 第43回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2011 (2011年7月7日-8日. 早稲田大学国際会議場) 東京
Document TypeConference Paper
JAXA Category特別資料
ISSN1349-113X
NCIDAA11984031
SHI-NOAA0065207039
Report NoJAXA-SP-11-015
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/15228


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