Flox/Kerosene
Propellant
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Flox/Kerosene propellant. FLOx was a mixture of liquid fluorine and liquid oxygen. Formulations of 70% liquid fluorine and 30% liquid fluorine with liquid oxygen were tested in Atlas rocket engines in the 1950's and 1960's. It improved performance while avoiding the extreme handling problems of pure liquid fluorine. Although tested in Atlas booster engines with regular RP-1 kerosene, it did not find operational use.
Propellant Formulation: Flox70/RP-1. or Flox30/RP-1. Optimum Oxidizer to Fuel Ratio: 3.8. Temperature of Combustion: 4,585 deg K. Density: 1.20 g/cc. Fuel Density: 0.806 g/cc. Fuel Freezing Point: -73 deg C. Fuel Boiling Point: 147 deg C.