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The S-IB stage was the first stage of the Saturn IB launch vehicle, which was used for Earth orbital missions.[2] It was an upgraded version of the S-I stage used on the earlier Saturn I rocket and was composed of nine propellant containers, eight fins, a thrust structure assembly, eight H-1rocket engines, and many other components. It also contained the ODOP transponder. The propellant containers consisted of eight Redstone-derived tanks (four holding liquid oxygen (LOX) and four holding RP-1) clustered around a Jupiter rocket-derived tank containing LOX. The four outboard engines gimballed to steer the rocket in flight, which required a few more engine components. The S-IB burned for nearly 2.5 minutes before separating at an altitude of 42 miles (68 km).
Fuel: RP-1 (Refined kerosene) 41,000 US gal (155 m3)
Oxidizer: Liquid oxygen (LOX) 66,277 US gal (251 m3) nominal capacity including 1.5% ullage volume (43,284 US gal / 163 m3 in four outer tanks plus 22,993 US gal / 87 m3 in center tank[3])
^ abcdKyle, Ed (December 6, 2012). "Saturn IB History". Space Launch Report . . . Saturn Vehicle History. Archived from the original on January 4, 2013. Retrieved 2014-09-01.((cite web)): CS1 maint: unfit URL (link)
^Wade, Mark (2001). "Saturn IB". Encyclopedia Astronautica. Archived from the original on May 4, 2002.