Theoretical Rocket Performance of JP-4 Fuel with Several Fluorine-oxygen Mixtures Assuming Equilibrium Composition
Title | Theoretical Rocket Performance of JP-4 Fuel with Several Fluorine-oxygen Mixtures Assuming Equilibrium Composition PDF eBook |
Author | Sanford Gordon |
Publisher | |
Pages | 78 |
Release | 1958 |
Genre | Aerodynamics |
ISBN |
Theoretical Rocket Performance of JP-4 Fuel with Several Fluorine-oxygen Mixtures Assuming Equilibrium Composition
Title | Theoretical Rocket Performance of JP-4 Fuel with Several Fluorine-oxygen Mixtures Assuming Equilibrium Composition PDF eBook |
Author | Sanford Gordon |
Publisher | |
Pages | 69 |
Release | 1958 |
Genre | Charts, diagrams, etc |
ISBN |
Theoretical rocket performance for equilibrium composition during expansion was calculated for JP-4 fuel with several fluorine-oxygen mixtures for a range of pressure ratios and oxidant-fuel ratios. The parameters included are specific impulse, combustion-chamber temperatures. Nozzle-exit temperature, molecular weight, characteristics velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, isentropic exponent, viscosity, thermal conductivity, and equilibrium gas compositions. A correlation is given for the effect of chamber pressure on several of the parameters.
Theoretical Rocket Performance of JP-4 Fuel with Several Fluorine-oxygen Mixtures Assuming Frozen Composition
Title | Theoretical Rocket Performance of JP-4 Fuel with Several Fluorine-oxygen Mixtures Assuming Frozen Composition PDF eBook |
Author | Sanford Gordon |
Publisher | |
Pages | 70 |
Release | 1957 |
Genre | Charts, diagrams, etc |
ISBN |
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.
Theoretical Performance of JP-4 Fuel with a 70-30 Mixture of Fluorine and Oxygen as a Rocket Propellant
Title | Theoretical Performance of JP-4 Fuel with a 70-30 Mixture of Fluorine and Oxygen as a Rocket Propellant PDF eBook |
Author | Sanford Gordon |
Publisher | |
Pages | 49 |
Release | 1956 |
Genre | |
ISBN |
Theoretical Rocket Performance of JP-4 Fuel with Mixtures of Liquid Ozone and Fluorine
Title | Theoretical Rocket Performance of JP-4 Fuel with Mixtures of Liquid Ozone and Fluorine PDF eBook |
Author | Vearl N. Huff |
Publisher | |
Pages | 22 |
Release | 19?? |
Genre | Aerodynamics |
ISBN |
Theoretical Performance of JP-4 Fuel with a 70-percent-fluorine - 30-percent Oxygen as a Rocket Propellant
Title | Theoretical Performance of JP-4 Fuel with a 70-percent-fluorine - 30-percent Oxygen as a Rocket Propellant PDF eBook |
Author | Sanford Gordon |
Publisher | |
Pages | 46 |
Release | 1956 |
Genre | Fluorine |
ISBN |
Theoretical Performance of JP-4 Fuel and Liquid Oxygen as a Rocket Propellant
Title | Theoretical Performance of JP-4 Fuel and Liquid Oxygen as a Rocket Propellant PDF eBook |
Author | Vearl N. Huff |
Publisher | |
Pages | 58 |
Release | 1956 |
Genre | Charts, diagrams, etc |
ISBN |
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.