LF2/Kerosene
Propellant
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LF2/Kerosene propellant. Use of fluorine with kerosene was studied in the 1950's, but performance was less than with other fuels, and no rocket engine reached test stage with this combination.
Optimum Oxidizer to Fuel Ratio: 2.8. Temperature of Combustion: 4,410 deg K. Ratio of Specific Heats: 1.22. Density: 1.23 g/cc. Characteristic velocity c: 1,950 m/s (6,390 ft/sec). Isp Shifting: 326 sec. Isp Frozen: 304 sec. Mol: 24.60 M (80.70 ft). Oxidizer Density: 1.510 g/cc. Oxidizer Freezing Point: -219 deg C. Oxidizer Boiling Point: -188 deg C. Fuel Density: 0.806 g/cc. Fuel Freezing Point: -73 deg C. Fuel Boiling Point: 147 deg C.