XLR89-5

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XLR89-5

Part of LR79

B2C/MA-1/MA-2
Credit: Boeing / Rocketdyne

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

Date: 1958. Number: 320 . Thrust: 758.70 kN (170,563 lbf). Specific impulse: 282 s. Specific impulse sea level: 248 s. Burn time: 135 s. Diameter: 2.45 m (8.03 ft).

Thrust (sl): 667.200 kN (149,993 lbf). Thrust (sl): 68,039 kgf. Engine: 643 kg (1,417 lb). Chamber Pressure: 40.00 bar. Area Ratio: 8. Propellant Formulation: Lox/RP-1. Thrust to Weight Ratio: 120.321928460342. Coefficient of Thrust vacuum: 1.73021886841794. Coefficient of Thrust sea level: 1.53021886841794.

Country: USA. Launch Vehicles: Atlas Able, Atlas B, Atlas C, Atlas D, Atlas Agena A, Atlas LV-3B / Mercury. Propellants: Lox/Kerosene. Stages: Atlas MA-2. Agency: Rocketdyne.

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