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Theoretical Performance of JP-4 Fuel and Liquid Oxygen as a Rocket Propellant
Vearl N. HuffAnthony FortiniSanford Gordon
其他書名
II. Equilibrium Composition
出版National Advisory Committee for Aeronautics, 1956
URLhttp://books.google.com.hk/books?id=oDsveQ0rZLsC&hl=&source=gbs_api
EBookFULL_PUBLIC_DOMAIN
註釋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 pressure.