@inproceedings{oai:jaxa.repo.nii.ac.jp:00016455,
 author = {伊集院, 恭弘 and 塚本, 真広 and 森田, 康平 and 荒木, 幹也 and 小島, 孝之 and 田口, 秀之 and 西田, 俊介 and 今村, 宰 and 志賀, 聖一 and 津江, 光洋 and Ijuin, Yasuhiro and Tsukamoto, Masahiro and Morita, Kohei and Araki, Mikiya and Kojima, Takayuki and Taguchi, Hideyuki and Nishida, Shunsuke and Imamura, Osamu and Shiga, Seiichi and Tsue, Mitsuhiro},
 book = {平成22年度宇宙輸送シンポジウム: 講演集録, Proceedings of Space Transportation Symposium: FY2010},
 month = {},
 note = {平成22年度宇宙輸送シンポジウム(2011年1月20-21日. 宇宙航空研究開発機構宇宙科学研究所), 相模原市, 神奈川県, Space Transportation FY2010 (January 20-21, 2011. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)(ISAS)), Sagamihara, Kanagawa Japan, Jet noise characteristics radiated from a rectangular plug nozzle of a pre-cooled turbojet engine are investigated, experimentally. In the present study, the nozzle scale (1.0 %, 2.4 %), total temperature (T(sub t) = 290 K-1720 K), afterburner (AB on or AB off), and hydrogen equivalence ratio (phi = 0.14 - 4.20) are varied. Temperature measurement was carried out using temperature measurement section. By use of A(U(sub j ))(exp n) law, normalized jet noise spectra are obtained. Normalized jet noise spectra with afterburner are lower than that for without afterburner. Combustion afterburner. Combustion afterburner. Combustion which takes place out of nozzle are dominant in a hydrogen rich burn afterburner. It is supposed that diffusion combustion of such an afterburner is dominant, and that the velocity index n=4 is more suitable, which corresponds to "monopole" sound source., 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: AA0065073008},
 publisher = {宇宙航空研究開発機構宇宙科学研究所, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)},
 title = {アフターバーナ当量比および断面温度分布が矩形プラグノズルからのジェット騒音に及ぼす影響},
 year = {2011}
}