N2O4/Hydyne
Propellant
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N2O4/Hydyne propellant. Hydyne was a propellant blend pushed rather vigorously by the Redstone arsenal in the late 1950's, but it found little application. This propellant combination was not used in any production rocket motors.
Optimum Oxidizer to Fuel Ratio: 2.71. Temperature of Combustion: 3,395 deg K. Density: 1.22 g/cc. Characteristic velocity c: 1,700 m/s (5,500 ft/sec). Isp Shifting: 282 sec. Isp Frozen: 271 sec. Oxidizer Density: 1.450 g/cc. Oxidizer Freezing Point: -11 deg C. Oxidizer Boiling Point: 21 deg C. Fuel Density: 0.860 g/cc. Fuel Freezing Point: -84 deg C. Fuel Boiling Point: 64 deg C.