@inproceedings{oai:jaxa.repo.nii.ac.jp:00004411,
 author = {中山, 智裕 and 佐藤, 哲也 and 橋本, 敦 and 小島, 孝之 and 田口, 秀之 and Nakayama, Tomohiro and Sato, Tetsuya and Hashimoto, Atsushi and Kojima, Takayuki and Taguchi, Hideyuki},
 book = {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},
 month = {Mar},
 note = {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, 43rd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2011 (July 7-8,  2011. Waseda University, International Conference Center), Tokyo Japan, Inlet 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., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0065207039, レポート番号: JAXA-SP-11-015},
 pages = {225--230},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 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},
 volume = {JAXA-SP-11-015},
 year = {2012}
}