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ClO3F/Kerosene
ClO3F/Kerosene propellant. No engines reached the operational stage using this propellant combination; perchloryl fluoride had better performance using hydrazine fuel. Rocket propellant RP-1, or its foreign equivalents, is a straight-run kerosene fraction.

Specific impulse: 280 s. Specific impulse sea level: 280 s.

Propellant Formulation: ClO3F/RP-1. Optimum Oxidizer to Fuel Ratio: 4.23. Temperature of Combustion: 3,675 deg K. Density: 1.25 g/cc. Oxidizer Density: 1.430 g/cc. Oxidizer Freezing Point: -146 deg C. Oxidizer Boiling Point: -47 deg C. Fuel Density: 0.806 g/cc. Fuel Freezing Point: -73 deg C. Fuel Boiling Point: 147 deg C.





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