PROPELLANT VAPORIZATION AS A CRITERION FOR ROCKET-ENGINE DESIGN:EXPERIMENTAL EFFECT OF COMBUSTOR LENGTH, THROAT DIAMETER, INJECTION VELOCITY, AND PRESSURE ON ROCKET COMBUSTOR EFFICIENCY

摘要

The efficiency of a heptanes-oxygen rocket combustor was measured for various combustor lengths, contraction ratios, and injection velocities of the heptanes. Combustor pressure varied concomitantly with these parameters. Plots of combustion efficiency with each of these combustor parameters show that efficiency increases with injection velocity, pressure, combustor length, and contraction ratio, except at some of the lower contraction ratios and injection velocities.