XLR-89-1

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

Manufacturer Name: MA-1. Government Designation: XLR89-1. Designer: Rocketdyne. Developed in: 1956. Application: Atlas A, B, C. Propellants: Lox/Kerosene. Thrust(vac): 758.700 kN (170,563 lbf). Thrust(sl): 667.200 kN (149,993 lbf). Isp: 282 sec. Isp (sea level): 248 sec. Burn time: 133 sec. Mass Engine: 725 kg (1,598 lb). Diameter: 1.53 m (5.00 ft). Chambers: 1. Chamber Pressure: 40.00 bar. Area Ratio: 8.00. Thrust to Weight Ratio: 106.71. Country: USA. Status: Out of production. First Flight: 1957. Last Flight: 1958. Flown: 16.

Designed for booster applications. Gas generator, pump-fed. Shared turbopumps for booster engines.

XLR-89-1 used on Rocket Stages

Used on stage: Atlas A. on launch vehicle: Atlas A.

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