@inproceedings{oai:jaxa.repo.nii.ac.jp:00016606,
 author = {塚本, 真広 and 福田, 将之 and 伊集院, 恭弘 and 荒木, 幹也 and 小島, 孝之 and 田口, 秀之 and 志賀, 聖一 and Tsukamoto, Masahiro and Fukuda, Masayuki and Ijuin, Yasuhiro and Araki, Mikiya and Kojima, Takayuki and Taguchi, Hideyuki and Shiga, Seiichi},
 book = {宇宙輸送シンポジウム: 講演集録, Proceedings of Space Transportation Symposium},
 month = {Jan},
 note = {平成21年度宇宙輸送シンポジウム(2010年1月14日-15日, 宇宙航空研究開発機構宇宙科学研究本部), Space Transportation Symposium (January 14-15, 2010. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)),  Sagamihara, Kanagawa Japan, Effects of injection conditions (nozzle geometry, working gas, and injection location) of aerodynamic tabs on supersonic jet noise from a rectangular plug nozzle were investigated, experimentally. In JAXA, a pre-cooled turbojet engine for hypersonic transport is under development. A 1/100-scaled model of the rectangular plug nozzle was used, and the supersonic jet noise reduction performance of aerodynamic tabs, which is small jet injection from the nozzle wall, was investigated. Take off condition of the aircraft were simulated, whose corresponding nozzle pressure ratio is 2.7. Aerodynamic tabs were used as a noise reduction device. There are two types of aerodynamic tab geometries, namely round and wedge nozzles. Air and helium were used as working gas of aerodynamic tabs. Several injection locations were tested. Sound pressure measurements were carried out. The wedge nozzle was more effective than round nozzle. Increasing the gas constant of working gas is effective for noise reduction. The most effective injection location was y = 4.0 mm., 形態: カラー図版あり, 形態: CD-ROM1枚, Physical characteristics: Original contains color illustrations, Note: One CD-ROM, 資料番号: AA0064741036},
 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 = {空力タブ噴射条件が超音速ジェット騒音に及ぼす効果},
 volume = {平成21年度},
 year = {2010}
}