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MON/UDMH
MON/UDMH propellant. No rocket engines went into production using this propellant combination.

Specific impulse: 338 s. Specific impulse sea level: 290 s.

Optimum Oxidizer to Fuel Ratio: 2.72. Temperature of Combustion: 3,490 deg K. Density: 1.14 g/cc. Oxidizer Density: 1.370 g/cc. Fuel Density: 0.793 g/cc. Fuel Freezing Point: -57 deg C. Fuel Boiling Point: 63 deg C.

Subtopics
MUT Rocketdyne MON/UDMH rocket engine. Satellite maneuvering motor. Developed 2005. New technology motor with improved thrust/weight ratio and use of mixed oxides of nitrogen oxidizer with a much lower freezing point than N2O4.
Engines: MUT.
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