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LR87-3
Part of LR87 Family
LR-87-3 Engine
LR-87-3 Engine
Credit: Bob Fortune
Aerojet LOx/Kerosene rocket engine. Titan 1 booster engine. Surplus Flight Engines were available for various uses in the 1960's. First flight 1959.

AKA: AJ23-130. Status: First flight 1959. Number: 140 . Thrust: 733.90 kN (164,987 lbf). Specific impulse: 290 s. Specific impulse sea level: 256 s. Burn time: 138 s. Height: 3.13 m (10.26 ft). Diameter: 1.53 m (5.00 ft).

Thrust (sl): 647.900 kN (145,654 lbf). Thrust (sl): 66,067 kgf. Engine: 839 kg (1,849 lb). Chamber Pressure: 40.00 bar. Area Ratio: 8. Thrust to Weight Ratio: 89.204410011919. Oxidizer to Fuel Ratio: 1.91. Coefficient of Thrust vacuum: 1.84532204931916. Coefficient of Thrust sea level: 1.64532204931916.



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

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