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- W2393047275 abstract "To better predict the regeneratively cooled liquid rocket engine thrust chamber heat transfer.Three dimensional numerical simulation was carried out for hot gas,solid wall and coolant coupled flow and heat transfer.The 9 steps with 6 specices chemical reaction model was used to simulate gas non-equilibrium chemical reactions.The radiative heat transfer was simulated with DO model.The coolant is supercritical hydrogen whose thermophysical properties are varied with both temperature and pressure.The results show that Redlich-Kwong equation of state,Peng-Robinson equation of state,Lucas method,TRAPP method can be used to predict hydrogen density,specific heat at constant pressure,viscosity,thermal conductivity,respectively.The simulated results using non-equilibrium flow are more accordant with real condition." @default.
- W2393047275 created "2016-06-24" @default.
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- W2393047275 date "2011-01-01" @default.
- W2393047275 modified "2023-09-24" @default.
- W2393047275 title "Numerical simulation of regeneraive cooling flow and heat transfer with nonequilibrium flow" @default.
- W2393047275 hasPublicationYear "2011" @default.
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