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Saturn II C-5A
Part of Saturn II Family
LOx/LH2 propellant rocket stage. Final common second stage design for Saturn C-3, C-4 and C-5 (November 1961). Developed into Saturn V second stage.

Status: Study 1961. Thrust: 4,446.65 kN (999,646 lbf). Gross mass: 384,057 kg (846,700 lb). Unfuelled mass: 31,740 kg (69,970 lb). Specific impulse: 420 s. Specific impulse sea level: 200 s. Burn time: 320 s. Height: 21.39 m (70.17 ft). Diameter: 10.06 m (33.00 ft). Span: 10.06 m (33.00 ft).

No Engines: 5.



Country: USA. Engines: J-2. Launch Vehicles: Saturn C-5, Saturn C-3B, Saturn C-4B, Saturn C-3BN, Saturn C-5N. Propellants: Lox/LH2.

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