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- W2314258204 abstract "Propellant performance of N2O/HTPB were studied firstly. Vacuum specific impulse is bound up with a oxidizer-to-fuel ratio and expansion ratio. Numerical solutions of full Navier-Stokes equations with chemical reaction flow were obtained for a nozzle flow of the N2O/HTPB hybrid rocket motor. Lower-Upper decomposition scheme and MUSCL-type and VanLeer approach were used. A chemical reaction model with 12 species and 16 elementary reactions was presented. The nozzle entrance condition was obtained by thermal calculation. The nozzle flow under optimum oxidizer-to-fuel ratio were calculated. which will be useful for the hybrid rocket motor design." @default.
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- W2314258204 date "2007-07-08" @default.
- W2314258204 modified "2023-10-05" @default.
- W2314258204 title "Computation of Nozzle Flow in a N2O/HTPB Hybrid Rocket Motor" @default.
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- W2314258204 doi "https://doi.org/10.2514/6.2007-5370" @default.
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