Investigation of Dual-Vortical-Flow Hybrid Rocket Engine without Flame Holding Mechanism
A 250 kgf thrust hybrid rocket engine was designed, tested, and verified in this work. Due to the injection and flow pattern of this engine, this engine was named dual-vortical-flow engine. This propulsion system uses N2O as oxidizer and HDPE as fuel. This engine was numerically investigated using a...
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| Autori principali: | , , , , , |
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| Natura: | Artigo |
| Lingua: | Inglês |
| Pubblicazione: |
Wiley
2018-01-01
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| Serie: | International Journal of Aerospace Engineering |
| Accesso online: | http://dx.doi.org/10.1155/2018/6513084 |
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