Theoretical Performance of JP-4 Fuel and Liquid Oxygen as a Rocket Propellant PDF Download
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Author: Vearl N. Huff Publisher: ISBN: Category : Charts, diagrams, etc Languages : en Pages : 58
Book Description
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.
Author: Vearl N. Huff Publisher: ISBN: Category : Charts, diagrams, etc Languages : en Pages : 58
Book Description
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.
Author: Sanford Gordon Publisher: ISBN: Category : Charts, diagrams, etc Languages : en Pages : 70
Book Description
Theoretical rocket performance for frozen composition during expansion was calculated for JP-4 fuel with several fluorine-oxygen mixtures for a large range of pressure ratios and oxidant-fuel ratios. The parameters included are specific impulse, combustion-chamber temperature, nozzle-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 for the effect of chamber pressure on several of the parameters.
Author: Vearl N. Huff Publisher: ISBN: Category : Charts, diagrams, etc Languages : en Pages : 22
Book Description
Data were estimated by means of a heat correction equation using data for JP-4 fuel with mixtures of oxygen and fluorine. The estimated data were checked for several cases by direct calculations. The difference in specific impulse between the estimated and directly calculated values was from 0.2 to 0.8 pound-second per pound. The maximum value of specific impulse was 334.9 pound-seconds per pound for a combustion-chamber pressure of 600 pounds per square inch absolute and an exit pressure of 1 atmosphere.
Author: Vearl N. Huff
Author: Vearl N. Huff
Author: Sanford Gordon
Author: Sanford Gordon
Author: Vearl N. Huff
Author: Sanford Gordon
Author: Sanford Gordon
Author: Sanford Gordon
Author: Sanford Gordon
Author: Gilbert K. Sievers
Author: Vearl N. Huff