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LR91-3
Part of LR91 Family
Aerojet LOx/Kerosene rocket engine. Development begun 1957. Titan 1 Stage 2 major production version. Proposed for second stage of Juno V-A, Super-Jupiter in 1959. Flown 1959-1965.

AKA: AJ23-131. Status: Flown 1959-1965.. Number: 70 . Thrust: 355.90 kN (80,010 lbf). Specific impulse: 308 s. Burn time: 225 s. Diameter: 2.26 m (7.41 ft).

Thrust (sl): 242.600 kN (54,539 lbf). Thrust (sl): 24,742 kgf. Engine: 590 kg (1,300 lb). Chamber Pressure: 45.00 bar. Area Ratio: 25. Thrust to Weight Ratio: 61.5050847457627. Coefficient of Thrust vacuum: 1.84091739925958. Coefficient of Thrust sea level: 1.28536184370403.



Country: USA. Launch Vehicles: Titan I, Super-Jupiter, Juno V-A. Propellants: Lox/Kerosene. Stages: Titan 1-2. Agency: Aerojet.

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