ClF3/Kerosene
Propellant
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ClF3/Kerosene propellant. No engines reached the operational stage using this propellant combination; chlorine trifluoride had better performance using hydrazine fuel. Rocket propellant kerosene RP-1 was a straight-run kerosene fraction.
Optimum Oxidizer to Fuel Ratio: 3.26. Temperature of Combustion: 3,505 deg K. Density: 1.41 g/cc. Characteristic velocity c: 1,575 m/s (5,167 ft/sec). Isp Shifting: 258 sec. Isp Frozen: 250 sec. Oxidizer Density: 1.830 g/cc. Oxidizer Freezing Point: -76 deg C. Oxidizer Boiling Point: 12 deg C. Fuel Density: 0.806 g/cc. Fuel Freezing Point: -73 deg C. Fuel Boiling Point: 147 deg C.