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- W1952122727 abstract "Theoretical values of performance parameters for liquid hydrogen and liquid fluorine as a rocket propellant were calculated on the assumption of equilibrium composition during the expansion process for a wide range of fuel-oxidant and expansion ratios. The parameters included were specific impulse, combustion-chamber temperature, nozzle-exit temperature, equilibrium composition, mean molecular weight, characteristic velocity, coefficient of thrust, ration of nozzle-exit area to throat area, specific heat at constant pressure, coefficient of viscosity, and coefficient of thermal conductivity. The maximum value of specific impulse was 364.6 pound-seconds per pound for a chamber pressure of 300 pounds per square inch absolute (20.41 atm) and an exit pressure of 1 atmosphere." @default.
- W1952122727 created "2016-06-24" @default.
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- W1952122727 date "1953-02-06" @default.
- W1952122727 modified "2023-09-26" @default.
- W1952122727 title "Theoretical Performance of Liquid Hydrogen and Liquid Fluorine as a Rocket Propellant" @default.
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