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- W2324257220 abstract "The industrial and scientific communities are devoting major research efforts to identify and assess critical technologies for new advanced propulsive concepts: combustion at high pressure, as well as the replacement of hydrogen with a hydrocarbon, has been assumed as a key issue to achieve better propulsive performances and lower environmental impact and to reduce the costs related to ground operations (propellant handling infrastructure and procedures) and increase flexibility. Starting from this background, the present work describes a CFD analysis (based on the numerical solution of RANS equations for chemically reacting flows) performed to evaluate the effects of different thermo-chemical modeling assumptions on the performances of a high-pressure LOx/CH4 rocket thrust chamber." @default.
- W2324257220 created "2016-06-24" @default.
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- W2324257220 date "2008-01-07" @default.
- W2324257220 modified "2023-10-16" @default.
- W2324257220 title "A CFD Method for Simulation of Mixing and Combustion in High-Pressure LOX/Methane Rocket Engines" @default.
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- W2324257220 doi "https://doi.org/10.2514/6.2008-949" @default.
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