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Saturn II C-5A
Part of Saturn II
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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