| タイトル | Multiple-cycle Simulation of a Pulse Detonation Engine Ejector |
| 本文（外部サイト） | http://hdl.handle.net/2060/20020090937 |
| 著者（英） | Perkins, H. D.; Yungster, S. |
| 著者所属（英） | NASA Glenn Research Center |
| 発行日 | 2002-10-01 |
| 言語 | eng |
| 内容記述 | This paper presents the results of a study involving single and multiple-cycle numerical simulations of various PDE-ejector configurations utilizing hydrogen-oxygen mixtures. The objective was to investigate the thrust, impulse and mass flow rate characteristics of these devices. The results indicate that ejector systems can utilize the energy stored in the strong shock wave exiting the detonation tube to augment the impulse obtained from the detonation tube alone. Impulse augmentation ratios of up to 1.9 were achieved. The axial location of the converging-diverging ejectors relative to the end of the detonation tube were shown to affect the performance of the system. |
| NASA分類 | Aircraft Propulsion and Power |
| レポートNO | AIAA Paper 2002-3630
E-13570
NAS 1.15:211888
ICOMP-2002-05
NASA/TM-2002-211888 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/65069 |
