Graduate School of Engineering, Gunma University
Graduate School of Engineering, Gunma University
Graduate School of Engineering, Gunma University
Faculty of Engineering, Gunma University
Aerospace Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA)(ARD)
Aviation Program Group, Japan Aerospace Exploration Agency (JAXA)(APG)
Faculty of Engineering, University of Tokyo
Faculty of Engineering, University of Tokyo
Faculty of Engineering, Gunma University
Faculty of Engineering, University of Tokyo
出版者
宇宙航空研究開発機構宇宙科学研究所
出版者（英）
Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)
雑誌名
平成22年度宇宙輸送シンポジウム: 講演集録
雑誌名(英)
Proceedings of Space Transportation Symposium: FY2010
Space Transportation FY2010 (January 20-21, 2011. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)(ISAS)), Sagamihara, Kanagawa Japan
抄録（英）
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.
内容記述
形態: カラー図版あり
形態: CD-ROM1枚
内容記述（英）
Physical characteristics: Original contains color illustrations
Note: One CD-ROM
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
