Nitric acid/Ammonia
Propellant
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Nitric acid/Ammonia propellant. No rocket engines with this propellant combination entered production.
Optimum Oxidizer to Fuel Ratio: 2.1. Temperature of Combustion: 2,690 deg K. Ratio of Specific Heats: 1.24. Density: 1.10 g/cc. Characteristic velocity c: 1,610 m/s (5,280 ft/sec). Isp Shifting: 260 sec. Isp Frozen: 255 sec. Mol: 21.00 M. Oxidizer Density: 1.510 g/cc. Oxidizer Freezing Point: -42 deg C. Oxidizer Boiling Point: 86 deg C. Fuel Density: 0.604 g/cc. Fuel Freezing Point: -78 deg C. Fuel Boiling Point: -33 deg C.