XLR-89-5

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

Manufacturer Name: MA-2. Government Designation: XLR89-5. Designer: Rocketdyne. Developed in: 1958. Application: Atlas D. 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: 135 sec. Mass Engine: 643 kg (1,417 lb). Diameter: 2.45 m (8.03 ft). Chambers: 1. Chamber Pressure: 40.00 bar. Area Ratio: 8.00. Thrust to Weight Ratio: 120.32. Country: USA. First Flight: 1958. Last Flight: 1967. Flown: 320.

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

XLR-89-5 used on Rocket Stages

Used on stage: Atlas MA-2. on launch vehicle: Atlas Able.

Used on stage: Atlas MA-2. on launch vehicle: Atlas B.

Used on stage: Atlas MA-2. on launch vehicle: Atlas C.

Used on stage: Atlas MA-2. on launch vehicle: Atlas D.

Used on stage: Atlas MA-2. on launch vehicle: Atlas LV-3A / Agena A.

Used on stage: Atlas MA-2. on launch vehicle: Atlas LV-3B / Mercury.

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