Energy Losses in High Energy Rocket Engines with Thrust Variation
Energy Losses in High Energy Rocket Engines with Thrust Variation
- Neue Suche nach: H. J. Sternfeld
- Neue Suche nach: H. J. Sternfeld
The effect of various parameters on the energy losses in the combustion chamber of oxygen/hydrogen, fluorine/hydrogen, and fluorine/ammonia rocket engines was investigated. A thrust variation of capacitatively cooled experimental rocket engines between 200 and 1,500 N was provided by a combustion chamber pressure variation between 3 and 15 bars. The energy losses of a fluorine/ammonia rocket engine were compared with results obtained with the distributed Energy Release-computer model. Results of the investigation are presented an two dimensional approximation functions. The energy losses of rocket engines with coaxial injectors can be described by the parameters MIXEFF and VAPTIME, which characterize the imperfect mixing and the incomplete vaporization of the propellants.
Dokumentinformationen
Energy Losses in High Energy Rocket Engines with Thrust Variation
1979
161 pages
Report
Keine Angabe
Englisch
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