Author: Sanford GordonPublisher:
ISBN:
Category :
Languages : en
Pages : 18
Book Description
Theoretical Maximum Performance of Liquid Fluorine-liquid Oxygen Mixture with JP-4 Fuel as Rocket Propellants
Author: Sanford GordonTheoretical Performance of JP-4 Fuel with a 70-percent-fluorine - 30-percent Oxygen as a Rocket Propellant
Author: Sanford GordonPublisher:
ISBN:
Category : Fluorine
Languages : en
Pages : 46
Book Description
Theoretical Rocket Performance of JP-4 Fuel with Mixtures of Liquid Ozone and Fluorine
Author: Vearl N. HuffPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 22
Book Description
Theoretical Rocket Performance of JP-4 Fuel with Several Fluorine-oxygen Mixtures Assuming Equilibrium Composition
Author: Sanford GordonPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 78
Book Description
Theoretical Rocket Performance of JP-4 Fuel with Several Fluorine-oxygen Mixtures Assuming Frozen Composition
Author: Sanford GordonPublisher:
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.
Theoretical Performance of JP-4 Fuel and Liquid Oxygen as a Rocket Propellant
Author: Vearl N. HuffPublisher:
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.
Handling and Use of Fluorine and Fluorine-oxygen Mixtures in Rocket Systems
Author: Harold W. SchmidtPublisher:
ISBN:
Category : Fluorine
Languages : en
Pages : 292
Book Description
Theoretical Rocket Performance of JP-4 Fuel with Mixtures of Liquid Ozone and Fluorine
Author: Vearl N. HuffPublisher:
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.
Theoretical Performance of JP-4 Fuel with a 70-30 Mixture of Fluorine and Oxygen as a Rocket Propellant
Author: Sanford GordonIndex of NACA Technical Publications
Author: United States. National Advisory Committee for AeronauticsPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 580
Book Description