Launch Vehicle

Launch Vehicle/Spacecraft Key Facts

	Apollo 7	Apollo 8	Apollo 9	Apollo 10	Apollo 11	Apollo 12	Apollo 13	Apollo 14	Apollo 15	Apollo 16	Apollo 17

First Stage (S-IB)
Contractor	Chrysler	---	---	---	---	---	---	---	---	---	---
Diameter, base, ft	21.500	---	---	---	---	---	---	---	---	---	---
Diameter, top, ft	21.667	---	---	---	---	---	---	---	---	---	---
Height, ft	80.200	---	---	---	---	---	---	---	---	---	---
Engines, type/number	H-1/8	---	---	---	---	---	---	---	---	---	---
Fuel	RP-1	---	---	---	---	---	---	---	---	---	---
Oxidizer	LO₂
Rated thrust each engine, lbf	200.000	---	---	---	---	---	---	---	---	---	---
Rated thrust total, lbf	1,600,000	---	---	---	---	---	---	---	---	---	---
Thrust at 35 to 38 sec, lbf	1,744,400	---	---	---	---	---	---	---	---	---	---

First Stage (S-IC)
Contractor	---	Boeing	Boeing	Boeing	Boeing	Boeing	Boeing	Boeing	Boeing	Boeing	Boeing
Diameter, base, ft	---	33.000	33.000	33.000	33.000	33.000	33.000	33.000	33.000	33.000	33.000
Diameter, top, ft	---	33.000	33.000	33.000	33.000	33.000	33.000	33.000	33.000	33.000	33.000
Height, ft	---	138.030	138.030	138.030	138.030	138.030	138.030	138.030	138.030	138.030	138.030
Engines, type/number	---	F-1/5	F-1/5	F-1/5	F-1/5	F-1/5	F-1/5	F-1/5	F-1/5	F-1/5	F-1/5
Fuel	---	RP-1	RP-1	RP-1	RP-1	RP-1	RP-1	RP-1	RP-1	RP-1	RP-1
Oxidizer	---	LO₂	LO₂	LO₂	LO₂	LO₂	LO₂	LO₂	LO₂	LO₂	LO₂
Rated thrust each engine, lbf	---	1,500,000	1,522,000	1,522,000	1,522,000	1,522,000	1,522,000	1,522,000	1,522,000	1,522,000	1,522,000
Rated thrust total, lbf	---	7,500,000	7,610,000	7,610,000	7,610,000	7,610,000	7,610,000	7,610,000	7,610,000	7,610,000	7,610,000
Thrust at 35 to 38 sec, lbf	---	7,560,000	7,576,000	7,536,000	7,552,000	7,594,000	7,560,000	7,504,000	7,558,000	7,620,000	7,599,000

Second Stage (S-II)
Contractor	---	North American Rockwell	North American Rockwell	North American Rockwell	North American Rockwell	North American Rockwell	North American Rockwell	North American Rockwell	North American Rockwell	North American Rockwell	North American Rockwell
Diameter, ft	---	33.000	33.000	33.000	33.000	33.000	33.000	33.000	33.000	33.000	33.000
Height, ft	---	81.500	81.500	81.500	81.500	81.500	81.500	81.500	81.500	81.500	81.500
Engines, type/number	---	J-2/5	J-2/5	J-2/5	J-2/5	J-2/5	J-2/5	J-2/5	J-2/5	J-2/5	J-2/5
Fuel	---	LH₂	LH₂	LH₂	LH₂	LH₂	LH₂	LH₂	LH₂	LH₂	LH₂
Oxidizer	---	LO₂	LO₂	LO₂	LO₂	LO₂	LO₂	LO₂	LO₂	LO₂	LO₂
Rated thrust each engine, lbf	---	225,000	230,000	230,000	230,000	230,000	230,000	230,000	230,000	230,000	230,000
Rated thrust total, lbf	---	1,125,000	1,150,000	1,150,000	1,150,000	1,150,000	1,150,000	1,150,000	1,150,000	1,150,000	1,150,000
Thrust, engine start command +61 sec, lbf	---	1,143,578	1,155,611	1,159,477	1,155,859	1,161,534	1,160,767	1,164,464	1,169,662	1,163,534	1,156,694
Thrust, outboard engine cutoff, lbf	---	865,302	730,000	642,068	625,751	611,266	635,725	580,478	548,783	787,380	787,009

Compiled from Saturn launch vehicle flight evaluation reports. Thrust for S-IC stage is at sea level and for the S-II and S-IVB stages is at altitude. Thrust listed at “35 to 38 sec”, “Engine Start Command + 61 seconds”, and at “Outboard Engine Cutoff” is actual thrust as flown.

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