Liquid methane/oxygen injector study for potential future Mars ascent
Author:
Affiliation:
1. NASA, Marshall Space Flight Center, Huntsville, AL
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.2000-3119
Reference21 articles.
1. Material compatibility and fuel cooling limit investigation for advanced LOX/hydrocarbon thrust chambers
2. Hydrocarbon-fuel/copper combustion chamber liner compatibility, corrosion prevention, and refurbishment
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3. Three-Dimensional Numerical Simulations of Low Frequency Combustion Instability in a LOX/Methane Rocket Engine;AIAA SPACE 2010 Conference & Exposition;2010-06-26
4. GOX/Methane Injector Effects on Combustion Efficiency;44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit;2008-07-21
5. Raman gas species measurements in hydrocarbon-fueled rocket engine injector flows;36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit;2000-07-24
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