LR89-7

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LR89-7

Part of LR79

MA-5
Credit: Boeing / Rocketdyne

Rocketdyne LOx/Kerosene rocket engine. Atlas space launchers. Out of production. Designed for booster applications. Gas generator, pump-fed. Shared turbopumps for booster engines. Evolved from MA-2 ICBM system. First flight 1963.

AKA: MA-5. Status: Out of production. Date: 1960. Number: 198 . Thrust: 948.00 kN (213,118 lbf). Specific impulse: 294 s. Specific impulse sea level: 259 s. Burn time: 174 s. Height: 3.40 m (11.10 ft). Diameter: 1.53 m (5.00 ft).

Thrust (sl): 835.100 kN (187,738 lbf). Thrust (sl): 85,162 kgf. Engine: 712 kg (1,569 lb). Chamber Pressure: 42.00 bar. Area Ratio: 8. Propellant Formulation: Lox/RP-1. Thrust to Weight Ratio: 135.867884750527. Oxidizer to Fuel Ratio: 2.25. Coefficient of Thrust vacuum: 1.53013234508252. Coefficient of Thrust sea level: 1.34831416326433.

Country: USA. Launch Vehicles: Atlas Centaur LV-3C, Atlas Agena D, Atlas Centaur D, Atlas F/Agena D, Atlas H, Atlas G Centaur, Atlas I. Propellants: Lox/Kerosene. Stages: Atlas MA-5. Agency: Rocketdyne.

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