H2O2/Solid
Propellant
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H2O2/Solid propellant. Hydrogen peroxide was proposed as the oxidizer in a hybrid rocket combination. No production engines resulted; safer nitrous oxide became the preferred oxidizer for such rockets.
Optimum Oxidizer to Fuel Ratio: 0.84. Temperature of Combustion: 3,470 deg K. Density: 1.39 g/cc. Characteristic velocity c: 1,785 m/s (5,856 ft/sec). Isp Shifting: 294 sec. Oxidizer Density: 1.440 g/cc. Oxidizer Freezing Point: -1 deg C. Oxidizer Boiling Point: 150 deg C. Fuel Density: 1.350 g/cc.