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LF2/LH2
LF2/LH2 propellant. This was theoretically the highest-performance propellant combination. However although test engines were built in both the United States and Russia, fluorine was found to be just too toxic and reactive to be safely used as a propellant.

Specific impulse: 470 s. Specific impulse sea level: 410 s. Location: 2545.

Optimum Oxidizer to Fuel Ratio: 8. Temperature of Combustion: 3,960 deg K. Ratio of Specific Heats: 1.33. Density: 0.46 g/cc. Characteristic velocity c: 2,545 m/s (8,349 ft/sec). Isp Shifting: 410 sec. Isp Frozen: 398 sec. Mol: 12.00 M (39.00 ft). Oxidizer Density: 1.510 g/cc. Oxidizer Freezing Point: -219 deg C. Oxidizer Boiling Point: -188 deg C. Fuel Density: 0.071 g/cc. Fuel Freezing Point: -259 deg C. Fuel Boiling Point: -253 deg C.



Subtopics

RD-350 Glushko exotic LF2/LH2 rocket engine. Design concept 1963-. Studied by Glushko as engine concept with high-energy propellants.

X-430 GE exoticLF2/LH2 rocket engine. Developed 1960's. Very high energy engine developed in early 1960's for future large upper stages. Not flown due to toxicity of propellants.

Engines: RD-350, X-430.

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