Specific impulse: 422 s. Specific impulse sea level: 363 s. Location: 2220.
Optimum Oxidizer to Fuel Ratio: 2.18. Temperature of Combustion: 4,660 deg K. Ratio of Specific Heats: 1.33. Density: 1.31 g/cc. Characteristic velocity c: 2,220 m/s (7,280 ft/sec). Isp Shifting: 364 sec. Isp Frozen: 334 sec. Mol: 19.40 M (63.60 ft). Oxidizer Density: 1.510 g/cc. Oxidizer Freezing Point: -219 deg C. Oxidizer Boiling Point: -188 deg C. Fuel Density: 1.008 g/cc. Fuel Freezing Point: 2.00 deg C. Fuel Boiling Point: 113 deg C.
|Chariot Bell exotic LF2/Hydrazine rocket engine. Titan 3 upper stage. Developed 1960's. Engine developed for high-energy replacement of Titan 3 transtage in late 1950's / early 1960's. Not flown due to toxicity of propellants.|
|G-1 engine Rocketdyne exotic LF2/Hydrazine rocket engine. Atlas upper stage. Developed 1960's. Engine developed for replacement of Agena upper stage in late 1950's. Not flown due to toxicity of propellants. NOMAD Upper Stage System. Pressure-fed.|