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Atlas MA-5
Part of Atlas MA engine series Family
LOx/Kerosene propellant rocket stage. .

Status: Out of production. Thrust: 1,896.01 kN (426,240 lbf). Gross mass: 3,646 kg (8,038 lb). Unfuelled mass: 3,646 kg (8,038 lb). Specific impulse: 294 s. Specific impulse sea level: 259 s. Burn time: 174 s. Diameter: 4.90 m (16.00 ft). Span: 4.90 m (16.00 ft).

No Engines: 2.



Country: USA. Engines: LR89-7. Launch Vehicles: Atlas Agena D, Atlas SLV-3C Centaur, Atlas SLV-3A Agena D, Atlas SLV-3D Centaur, Atlas H, Atlas G Centaur, Atlas I. Propellants: Lox/Kerosene.

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