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N2O4/Kerosene

Propellant

Original archive entry. The text, images and links below are kept as they were written.

N2O4/Kerosene propellant. This low-cost propellant combination was used in the Otrag low-cost modular rocket system, flight-tested 1977-1983.

Optimum Oxidizer to Fuel Ratio: 4.04. Temperature of Combustion: 3,445 deg K. Density: 1.25 g/cc. Characteristic velocity c: 1,660 m/s (5,440 ft/sec). Isp Shifting: 276 sec. Isp Frozen: 264 sec. Oxidizer Density: 1.450 g/cc. Oxidizer Freezing Point: -11 deg C. Oxidizer Boiling Point: 21 deg C. Fuel Density: 0.806 g/cc. Fuel Freezing Point: -73 deg C. Fuel Boiling Point: 147 deg C.

Subtopics

  • Otrag CPRU N2O4/Kerosene propellant rocket stage. Clustered to form Otrag launch vehicles. Pressure-fed, using cheapest possible propellants.

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