XLR89-1

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XLR89-1

Part of LR79

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

Rocketdyne LOx/Kerosene rocket engine. Atlas A, B, C. Out of production. Designed for booster applications. Gas generator, pump-fed. Shared turbopumps for booster engines. First flight 1957.

AKA: MA-1. Status: Out of production. Date: 1956. Number: 16 . Thrust: 758.70 kN (170,563 lbf). Specific impulse: 282 s. Specific impulse sea level: 248 s. Burn time: 133 s. Diameter: 1.53 m (5.00 ft).

Thrust (sl): 667.200 kN (149,993 lbf). Thrust (sl): 68,038 kgf. Engine: 725 kg (1,598 lb). Chamber Pressure: 40.00 bar. Area Ratio: 8. Propellant Formulation: Lox/RP-1. Thrust to Weight Ratio: 106.712413793104. Coefficient of Thrust vacuum: 1.73020768652599. Coefficient of Thrust sea level: 1.53020768652599.

Country: USA. Launch Vehicles: Atlas A. Propellants: Lox/Kerosene. Stages: Atlas A stage. Agency: Rocketdyne.

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