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ClF3/Hydrazine
ClF3/Hydrazine propellant. Chlorine trifluoride was another of the extremely reactive and toxic oxidizers tested in the United States in the late 1950's. This was the highest performance propellant using ClF3. Methods of storing and using it were developed, and it found application in Rocketdyne engines for missiles and anti-ballistic missile interceptors in the 1990's. Hydrazine (N2H4) produced better specific impulse when used with ClF3 than the UDMH fuel commonly used in other applications.

Specific impulse: 338 s. Specific impulse sea level: 294 s. Location: 1825.

Optimum Oxidizer to Fuel Ratio: 2.77. Temperature of Combustion: 3,895 deg K. Ratio of Specific Heats: 1.33. Density: 1.51 g/cc. Characteristic velocity c: 1,825 m/s (5,987 ft/sec). Isp Shifting: 294 sec. Isp Frozen: 281 sec. Mol: 23.00 M (75.00 ft). Oxidizer Density: 1.830 g/cc. Oxidizer Freezing Point: -76 deg C. Oxidizer Boiling Point: 12 deg C. Fuel Density: 1.008 g/cc. Fuel Freezing Point: 2.00 deg C. Fuel Boiling Point: 113 deg C.



Subtopics

FLEXEM Rocketdyne exotic ClF3/Hydrazine rocket engine. Flexible Energy Management. Pressure-fed. Sustainer 267-4000 lb thrust vacuum, specific impulse 260 seconds.

RS-19 Rocketdyne exotic ClF3/Hydrazine rocket engine. Condor Development Booster Air-to-Ground Missile. Pressure-fed. Thrust and specific impulse values are at sea level.

Engines: FLEXEM, RS-19.

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