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LF2/Hydrazine
LF2/Hydrazine propellant. In the United States. In the 1960's the USAF sponsored development of engines by Bell and Rocketdyne using this propellant combination to power high-performance upper stages to replace the Agena and Transtage on the Atlas and Titan launch vehicles. However although test engines were built, fluorine was found to be just too toxic and reactive to be safely used as a propellant.

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.



Subtopics

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.

Engines: G-1 engine, Chariot.

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