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LR87-7
Part of LR87
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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