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Saturn IVB C-5A
Part of Saturn IV Family
LOx/LH2 propellant rocket stage. Final common third stage design for Saturn C-4 and C-5 (November 1961). Developed into Saturn V second stage. After development started, decision taken to boost performance by increasing diameter to 6.61 m and increasing propellant load.

Status: Study 1961. Thrust: 889.33 kN (199,928 lbf). Gross mass: 102,249 kg (225,420 lb). Unfuelled mass: 11,563 kg (25,492 lb). Specific impulse: 420 s. Specific impulse sea level: 200 s. Burn time: 415 s. Height: 19.00 m (62.00 ft). Diameter: 5.59 m (18.33 ft). Span: 5.59 m (18.33 ft).



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

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