Experimental investigation of momentum and heat transfer in pulse detonation rockets

J. Kasahara, Y. Tanahashi, M. Hirano, T. Numata, A. Matsuo, T. Ende

研究成果: Paper査読

3 被引用数 (Scopus)

抄録

The thrust performance and heat transfer in an ethylene-oxygen single tube pulse detonation rocket (PDR), were analyzed. The thrust data were obtained by two measurement devices including, a laser displacement sensor and a load cell. The time average thrusts were 122.2 N (10 Hz) and 130.3 N (12.5 Hz), which were corresponding to 293.7 and 321.2 seconds of effective specific impulses, respectively. It was found that the total heat flux in the wall of the PDR tubes was 400 kW/m2.

本文言語English
ページ11158-11167
ページ数10
出版ステータスPublished - 2004 7 1
イベント42nd AIAA Aerospace Sciences Meeting and Exhibit - Reno, NV, United States
継続期間: 2004 1 52004 1 8

Other

Other42nd AIAA Aerospace Sciences Meeting and Exhibit
国/地域United States
CityReno, NV
Period04/1/504/1/8

ASJC Scopus subject areas

  • 工学(全般)

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