Theoretical performance of JP-4 fuel and liquid oxygen as a rocket propellant II : equilibrium composition

Huff, Vearl N Fortini, Anthony Gordon, Sanford
naca-rm-e56d23
September 07, 1956


Data were calculated for equivalence ratios of 1 to 3, chamber pressures of 300 and 600 pounds per square inch absolute, and pressure ratios of 1 to 1500. Parameters included are specific impulse, combustion and exit temperature, molecular weight, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, isentropic exponent, viscosity, and thermal conductivity. A correlation is given which permits determination of performance for a wide range of chamber pressures.

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