Saturn C-8

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Saturn C-8

Saturn C-8 Launch Vehicle
Fact sheet
Function	Heavy Manned Launch vehicle
Manufacturer	Never Assigned
Country of origin	USA
Cost per Launch (1985)	c. $58,300,000 (USD)
Size
Height	131m
Diameter	12.19m
Mass	4,770,260kg
Stages	3
	Capacity
Payload to LEO	210,000kg
Launch History
Status	Unbuilt
Launch Sites	Kennedy Space Center
Total launches	0
First Stage - Increased Diameter S-IC
Engines	8 F-1
Thrust	6,314,600kgf
Specific Impulse	304sec
Burn time	157 seconds
Fuel	LOX/Kerosene
Second Stage - Increased Diameter S-II
Engines	8 J-2
Thrust	842,822kgf
Specific Impulse	425sec
Burn time	306sec
Fuel	LOX/LH2
Third Stage - S-IVB Stretch (Details not available, description is for standard S-IVB)
Engines	1 Rocketdyne J-2
Thrust	1 MN (225,000 lbf)
Burn time	165 + 335 seconds (2 burns)
Fuel	LH2/LOX

The Saturn C-8 was the largest Saturn rocket to be designed. It was an alternative to the Nova rocket, should a direct landing method of lunar exploration have been chosen by NASA for the Apollo program. The first stage was an increased diameter version of the S-IC. The second stage was an increased diameter S-II stage. Both of these had eight engines, as opposed to the standard five. The third stage was a stretched S-IVB stage, which still retained its original diameter and engines.

Eventually, the Lunar Orbit Rendezvous concept rendered the C-8 obsolete, and the smaller Saturn C-5 was developed instead under the designation "Saturn V", as the LOR spacecraft was within its payload capacity.

The C-8 was never taken further than the design process as it was too big and costly.