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B2C/MA-1/MA-2
Credit - Boeing / Rocketdyne
Engine Model: LR89-5. Manufacturer Name: MA-3. Government Designation: LR89-5. Designer: Rocketdyne. Developed in: 1958. Application: Atlas E, F. Propellants: Lox/Kerosene. Thrust(vac): 822.500 kN (184,905 lbf). Thrust(sl): 726.000 kN (163,211 lbf). Isp: 290 sec. Isp (sea level): 256 sec. Burn time: 120 sec. Mass Engine: 720 kg (1,580 lb). Diameter: 1.53 m (5.00 ft). Length: 3.40 m (11.10 ft). Chambers: 1. Chamber Pressure: 41.00 bar. Area Ratio: 8.00. Oxidizer to Fuel Ratio: 2.25. Thrust to Weight Ratio: 116.49. Country: USA. First Flight: 1960. Last Flight: 1995. Flown: 504.

Designed for booster applications. Gas generator, pump-fed. Separate turbopumps for each booster engine.

Engine Model: LR89-7. Manufacturer Name: MA-5. Government Designation: LR89-7. Designer: Rocketdyne. Developed in: 1960. Application: Atlas space launchers. Propellants: Lox/Kerosene. Thrust(vac): 948.000 kN (213,118 lbf). Thrust(sl): 835.100 kN (187,738 lbf). Isp: 294 sec. Isp (sea level): 259 sec. Burn time: 174 sec. Mass Engine: 712 kg (1,569 lb). Diameter: 1.53 m (5.00 ft). Length: 3.40 m (11.10 ft). Chambers: 1. Chamber Pressure: 42.00 bar. Area Ratio: 8.00. Oxidizer to Fuel Ratio: 2.25. Thrust to Weight Ratio: 135.87. Country: USA. Status: Out of production. First Flight: 1963. Last Flight: 1997. Flown: 198.

Designed for booster applications. Gas generator, pump-fed. Shared turbopumps for booster engines. Evolved from MA-2 ICBM system.

Engine Model: RS-56-OBA. Manufacturer Name: MA-5A. Designer: Rocketdyne. Developed in: 1988. Propellants: Lox/Kerosene. Thrust(vac): 1,046.800 kN (235,330 lbf). Thrust(sl): 920.800 kN (207,004 lbf). Isp: 299 sec. Isp (sea level): 263 sec. Burn time: 172 sec. Mass Engine: 805 kg (1,774 lb). Diameter: 2.45 m (8.03 ft). Length: 3.43 m (11.25 ft). Chambers: 1. Chamber Pressure: 48.00 bar. Area Ratio: 8.00. Oxidizer to Fuel Ratio: 2.25. Thrust to Weight Ratio: 132.30. Country: USA. Status: Out of production. First Flight: 1991. Last Flight: 2004. Flown: 126.

Designed for booster applications. Gas generator, pump-fed.

Engine Model: XLR89-1. 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.

Engine Model: XLR89-5. 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.

LR89 used on Rocket Stages
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