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Wall heat transfer analysis are of primary importance in liquid rocket engine design. The contribution of radiative heat flux is evaluated for two pairs of propellants (hydrogen/oxygen and methane/oxygen). Operating conditions where its role becomes importance are identified and a tool for quick preliminary evaluation is proposed.

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This page is a summary of: Numerical Investigation on Radiative Heat Loads in Liquid Rocket Thrust Chambers, Journal of Propulsion and Power, September 2019, American Institute of Aeronautics and Astronautics (AIAA),
DOI: 10.2514/1.b37536.
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