Abstract
A combustion flow inside a film -cooled bipropellant thruster was simulated numerically. The film -cooled bipropellant thruster model include d a reduced detail kinetic reaction model of hydrazine fuel and di -nitrogen tetroxide (NTO) oxidizer composed of 61 elementary reactions. This kinetic reaction model had been origin ally composed of 245 elementary reactions and was developed to be available for CFD simulations. Also bipropellant thruster model included droplet motion and evaporation mechanism so that it could simulate the gas generation with turbulent flow field. The flow simulation results show ed the flame structure and film -cooled mechanism in detail and could explain the film -cooling dry out mechanism in accordance with experimental results.
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