Nitric acid/Hydyne
Propellant
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Nitric acid/Hydyne propellant. Hydyne was a propellant blend pushed rather vigorously by the Redstone arsenal in the late 1950's, but it found little application. No rocket engines with this propellant combination entered production.
Optimum Oxidizer to Fuel Ratio: 3.11. Temperature of Combustion: 3,195 deg K. Density: 1.31 g/cc. Oxidizer Density: 1.510 g/cc. Oxidizer Freezing Point: -42 deg C. Oxidizer Boiling Point: 86 deg C. Fuel Density: 0.860 g/cc. Fuel Freezing Point: -84 deg C. Fuel Boiling Point: 64 deg C.