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LR87-11

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AKA: AJ23-139. Status: Out of production. Number: 534 . Thrust: 1,218.80 kN (273,997 lbf). Specific impulse: 302 s. Specific impulse sea level: 250 s. Burn time: 200 s. Height: 3.84 m (12.59 ft). Diameter: 1.14 m (3.74 ft).

Replacing the 9 model, this is the only engine - together with its stage 2 derivative - to be operated on storable propellants as well as LOX/kerosene and tested on LOX/LH2.. Manufacturer: Aerojet Propulsion Division. Applications: Titan 3 & 4 stage 1. First Flown: 1968 Titan 3, 1989 Titan 4. Dry Mass: 2281 kg (paired), 758 kg (single). Length: 3.84 m to top of thrust structure, 3.13 m to top of turbopump assembly. Maximum Diameter: 1.14 m. Mounting: fixed pair. Engine Cycle: gas generator. Oxidizer: nitrogen tetroxide at 540.7 kg/sec. Fuel: Aerozine-50 at 284 kg/sec. Mixture Ratio (O/F). 1.91:1. Thrust: 2437.5 kN vacuum paired. Isp: 301 sec vacuum. Expansion Ratio: 15:1. Combustion Chamber Pressure: 58.3 atm. Cooling Method: fuel regenerative & ablative skirt. Used in Titan 4-1; Titan 3B-1; Titan 3A-1.

Thrust (sl): 968.400 kN (217,705 lbf). Thrust (sl): 98,754 kgf. Engine: 758 kg (1,671 lb). Chamber Pressure: 59.10 bar. Area Ratio: 15. Thrust to Weight Ratio: 163.955030945495. Oxidizer to Fuel Ratio: 1.91. Coefficient of Thrust vacuum: 3.03319858090835. Coefficient of Thrust sea level: 2.77590870097696.