XLR105-5

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XLR105-5

Part of LR105

MA-3
Credit: Boeing / Rocketdyne

Rocketdyne LOx/Kerosene rocket engine. Atlas D. Atlas Sustainer. Gas generator, pump-fed. Shared turbopumps for booster engines. First flight 1958.

AKA: MA-2. Date: 1958. Number: 172 . Thrust: 363.20 kN (81,651 lbf). Specific impulse: 309 s. Specific impulse sea level: 215 s. Burn time: 335 s. Diameter: 3.05 m (10.00 ft).

Thrust (sl): 252.700 kN (56,809 lbf). Thrust (sl): 25,771 kgf. Engine: 460 kg (1,010 lb). Chamber Pressure: 48.00 bar. Area Ratio: 25. Propellant Formulation: Lox/RP-1. Thrust to Weight Ratio: 80.5173913043478. Coefficient of Thrust vacuum: 1.73727457790893. Coefficient of Thrust sea level: 1.21644124457559.

Country: USA. Launch Vehicles: Atlas Able, Atlas B, Atlas C, Atlas Centaur LV-3C, Atlas D, Atlas Agena A, Atlas LV-3B / Mercury. Propellants: Lox/Kerosene. Stages: Atlas Able stage, Atlas Centaur LV-3C stage, Atlas Agena LV-3A, Atlas B stage, Atlas D stage. Agency: Rocketdyne.

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