Saturn C-8

Infobox rocket
name = Saturn C-8

---

imsize = 70
caption = Saturn C-8 Launch Vehicle
function = Heavy Manned Launch vehicle
manufacturer = Never Assigned
country-origin = United States
cpl-year = 1985
cpl = c. $58,300,000 (USD)
height = 131m
alt-height =
diameter = 12.19 m
alt-diameter =
mass = 4,770,260 kg
alt-mass =
stages = 3
LEO-payload = 210,000 kg
alt-LEO =
payload-location Translunar
payload = 74,000 kg
alt-payload =
payload-location2 =
payload2 =
alt-payload2 =
status = Unbuilt
sites = Kennedy Space Center
launches = 0
stage1name = Increased Diameter S-IC
stage1engines = 8 F-1
stage1thrust = 6,314,600 kg_f
alt-stage1thrust = 61.925 kN
stage1SI = 304 s (3.02 kN·s/kg)
stage1time = 157 seconds
stage1fuel = LOX/Kerosene
stage2name = Increased Diameter S-II
stage2engines = 8 J-2
stage2thrust = 842,822 kg_f
alt-stage2thrust = 8,265.26 kN
stage2SI = 425 s (4.17 kN·s/kg)
stage2time = 306 s
stage2fuel = LOX/LH2
stage3name = S-IVB Stretch
(Details not available, description is for standard S-IVB)
stage3engines = 1 Rocketdyne J-2
stage3thrust = 1 MN
alt-stage3thrust = 225,000 lb_f
stage3time = 165 + 335 seconds
(2 burns)
stage3fuel = 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.