@inproceedings{oai:jaxa.repo.nii.ac.jp:00003628,
 author = {佐藤, 寛太 and 沢田, 恭兵 and 生沼, 秀司 and 石井, 達哉 and 金子, 成彦 and Sato, Kanta and Sawada, Kyohei and Oinuma, Hideshi and Ishii, Tatsuya and Kaneko, Shigehiko},
 book = {宇宙航空研究開発機構特別資料: 第47回流体力学講演会/第33回航空宇宙数値シミュレーション技術シンポジウム論文集, JAXA Special Publication: Proceedings of the 47th Fluid Dynamics Conference / the 33rd Aerospace Numerical Simulation Symposium},
 month = {Mar},
 note = {第47回流体力学講演会/第33回航空宇宙数値シミュレーション技術シンポジウム (2015年7月2日-3日. 東京大学生産技術研究所), 目黒区, 東京, 47th Fluid Dynamics Conference /the 33rd Aerospace Numerical Simulation Symposium (July 2-3, 2015. Institute of Industrial Science , the University of Tokyo), Meguro-ku, Tokyo, Japan, It is known that the microjet blowing secondary air to the jet shear layer is effective in reducing jet mixing noise. One of the considerations for the microjet is a nozzle shape for injecting the secondary air. In the previous studies, the flow rate and the arrangements of microjet nozzles under cold jet were investigated. Considering the application of the microjet to the actual engine, however, it is necessary to grasp the acoustic characteristics under heated jet. In this paper, we applied the microjet nozzle of annular slit shape to the model-scale turbojet engine with changing the split number and cross sectional area of microjet and evaluated the far-field noise reduction effect., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1630005003, レポート番号: JAXA-SP-15-013},
 pages = {29--33},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {環状スリットノズルからの二次空気によるジェット騒音低減の試み},
 volume = {JAXA-SP-15-013},
 year = {2016}
}