H2-O2 supercritical combustion modeling using a CFD code
The characteristics of propellant injection, mixing, and combustion have a profound effect on liquid rocket engine performance. The necessity of raising rocket engines performance requires a combustion chamber operation often in a supercritical regime. A supercritical combustion model based on a one...
| Main Authors: | , |
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| Format: | Article |
| Language: | English |
| Published: |
VINCA Institute of Nuclear Sciences
2009-01-01
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| Series: | Thermal Science |
| Subjects: | |
| Online Access: | http://www.doiserbia.nb.rs/img/doi/0354-9836/2009/0354-98360903139B.pdf |