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title予冷ターボエンジン用エアインテークの遷音速非定常特性に関する風洞試験
Other TitleWind Tunnel Experiment on Supersonic Instability of Pre-cooled Turbo Jet Engine Inlet
Author(jpn)宮村, 圭太; 小川, 春陽; 林, 映里; 佐藤, 哲哉; 小島, 孝之; 田口, 秀之
Author(eng)Miyamura, Keita; Ogawa, Shunyo; Hayashi, Eri; Sato, Tetsuya; Kojima, Takayuki; Taguchi, Hideyuki
Author Affiliation(jpn)早稲田大学; 早稲田大学; 早稲田大学; 早稲田大学; 宇宙航空研究開発機構; 宇宙航空研究開発機構
Author Affiliation(eng)Waseda University; Waseda University; Waseda University; Waseda University; Japan Aerospace Exploration Agency (JAXA); Japan Aerospace Exploration Agency (JAXA)
Issue Date2009-12
PublisherInstitute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)
宇宙航空研究開発機構宇宙科学研究本部
Publication titleSymposium on Flight Mechanics and Astrodynamics
宇宙航行の力学シンポジウム
Volume平成20年度
Publication date2009-12
Languagejpn
eng
AbstractInlet buzz, a self-excited oscillation of shock-wave, is known to occur on supersonic/hypersonic inlets under subcritical condition in a supersonic/hypersonic flow. In this research, supersonic inlet buzz characteristics of JAXA's pre-cooled turbo jet engine, which is currently under development, was examined through wind tunnel testing. The resulting unsteady pressure data and high-speed schilieren pictures at Mach 1.7 to 2.2 show that the buzz oscillation frequency increased from 30 Hz to 40 Hz as the flow plug, which is placed just aft of the inlet to simulate the core engine, was closed thus effectively decreasing the captured mass flow. Schilieren pictures also indicate that Dailey type buzz was seen in this experiment.
DescriptionMeeting Information: Symposium on Flight Mechanics and Astrodynamics 2008 (December 4-5, 2008. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)), Sagamihara, Kanagawa Japan
会議情報: 宇宙航行の力学シンポジウム(平成20年度)(2008年12月4~5日、宇宙航空研究開発機構宇宙科学研究本部)
Document TypeConference Paper
JAXA Categoryシンポジウム・研究会
SHI-NOAA0064729029
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/19613


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