Theoretical Performance of JP-4 Fuel and Liquid Oxygen as a Rocket Propellant

Theoretical Performance of JP-4 Fuel and Liquid Oxygen as a Rocket Propellant
Author: Vearl N. Huff
Publisher:
Total 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.

Index of NACA Technical Publications

Index of NACA Technical Publications
Author: United States. National Advisory Committee for Aeronautics
Publisher:
Total Pages: 388
Release: 1959
Genre: Aeronautics
ISBN: