@inproceedings{oai:jaxa.repo.nii.ac.jp:00014452,
 author = {宮村, 圭太 and 小川, 春陽 and 林, 映里 and 佐藤, 哲哉 and 小島, 孝之 and 田口, 秀之 and Miyamura, Keita and Ogawa, Shunyo and Hayashi, Eri and Sato, Tetsuya and Kojima, Takayuki and Taguchi, Hideyuki},
 book = {宇宙航行の力学シンポジウム, Symposium on Flight Mechanics and Astrodynamics},
 month = {Dec},
 note = {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), 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, Inlet 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., 資料番号: AA0064729029},
 publisher = {宇宙航空研究開発機構宇宙科学研究本部, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)},
 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},
 volume = {平成20年度},
 year = {2009}
}