LR91-5

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LR91-5

Part of LR91

Aerojet N2O4/Aerozine-50 rocket engine. Titan 2 ICBM Stage 2. Out of Production. Scaled down version of stage 1 engine featuring fixed single chamber. Gas generator cycle. First flight 1962.

AKA: AJ23-133. Status: Out of Production. Date: 1962. Thrust: 444.80 kN (99,995 lbf). Specific impulse: 315 s. Burn time: 175 s. Height: 2.80 m (9.10 ft). Diameter: 1.68 m (5.51 ft).

Propellant flow rate: 163 kg/sec. Mixture Ratio: 1.80.

Engine: 500 kg (1,100 lb). Chamber Pressure: 56.20 bar. Area Ratio: 49.2. Thrust to Weight Ratio: 90.71. Oxidizer to Fuel Ratio: 1.8.

Family: Storable liquid. Country: USA. Launch Vehicles: Titan II. Propellants: N2O4/Aerozine-50. Agency: Aerojet.

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