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LR87-7
Part of LR87 Family
Aerojet N2O4/Aerozine-50 rocket engine. Study 1961. Version of LR-87-5 used on Gemini Titan 2 launch vehicle. Proposed for unflown Titan 3L2, Titan 3L4 boosters. First flight 1962.

AKA: AJ23-134. Status: First flight 1962.. Number: 212 . Thrust: 1,086.10 kN (244,165 lbf). Specific impulse: 296 s. Specific impulse sea level: 258 s. Burn time: 139 s. Height: 3.13 m (10.26 ft). Diameter: 1.53 m (5.00 ft).

Thrust (sl): 946.700 kN (212,827 lbf). Thrust (sl): 96,535 kgf. Engine: 713 kg (1,571 lb). Chamber Pressure: 47.00 bar. Area Ratio: 9. Thrust to Weight Ratio: 155.333800841515. Oxidizer to Fuel Ratio: 1.9. Coefficient of Thrust vacuum: 2.2310677081288. Coefficient of Thrust sea level: 1.97574855919263.



Family: Storable liquid. Country: USA. Launch Vehicles: Titan II, Titan 3L2, Titan 3L4. Propellants: N2O4/Aerozine-50. Stages: Titan 2-1, Titan LDC-1. Agency: Aerojet.

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