The S-IB stage was the first stage

Multistage rocket

A multistage rocket is a rocket that usestwo or more stages, each of which contains its own engines and propellant. A tandem or serial stage is mounted on top of another stage; a parallel stage is attached alongside another stage. The result is effectively two or more rockets stacked on top of or...

 of the Saturn IB

Saturn IB

The Saturn IB was an American launch vehicle commissioned by the National Aeronautics and Space Administration for use in the Apollo program...

 launch vehicle, which was used for Earth orbital missions. It was composed of nine propellant containers, eight fins, a thrust structure assembly, eight H-1

H-1 (rocket engine)

Rocketdyne's H-1 is a thrust liquid-propellant rocket engine burning LOX and RP-1. The H-1 was developed for use in the S-IB first stage of the Saturn I and Saturn IB rockets, where it was used in clusters of eight engines...

 rocket engine

Rocket engine

A rocket engine, or simply "rocket", is a jet engineRocket Propulsion Elements; 7th edition- chapter 1 that uses only propellant mass for forming its high speed propulsive jet. Rocket engines are reaction engines and obtain thrust in accordance with Newton's third law...

s, and many other components. The propellant containers consisted of eight Redstone tanks (four holding LOX

Lox

Lox is salmon fillet that has been cured. In its most popular form, it is thinly sliced—less than in thickness—and, typically, served on a bagel, often with cream cheese, onion, tomato, cucumber and capers...

 and four holding RP-1

RP-1

RP-1 is a highly refined form of kerosene outwardly similar to jet fuel, used as a rocket fuel. Although having a lower specific impulse than liquid hydrogen , RP-1 is cheaper, can be stored at room temperature, is far less of an explosive hazard and is far denser...

) clustered around a Jupiter rocket tank containing LOX. The four outboard engines gimballed, meaning they could be steered to guide the rocket. This required a few more engine components.

Specifications:

Height: 83.6 ft (25.5 m)

Diameter: 21.7 ft (6.6 m)

Number of fins: 8

Finspan: 18 ft (5.5 m)

Engines: 8 H-1

H-1 (rocket engine)

Rocketdyne's H-1 is a thrust liquid-propellant rocket engine burning LOX and RP-1. The H-1 was developed for use in the S-IB first stage of the Saturn I and Saturn IB rockets, where it was used in clusters of eight engines...

Thrust: 1,600,000 lbf (7.1 MN)

Fuel: RP-1

RP-1

RP-1 is a highly refined form of kerosene outwardly similar to jet fuel, used as a rocket fuel. Although having a lower specific impulse than liquid hydrogen , RP-1 is cheaper, can be stored at room temperature, is far less of an explosive hazard and is far denser...

 (Refined kerosene

Kerosene

Kerosene, sometimes spelled kerosine in scientific and industrial usage, also known as paraffin or paraffin oil in the United Kingdom, Hong Kong, Ireland and South Africa, is a combustible hydrocarbon liquid. The name is derived from Greek keros...

) 41,000 US gal (155 m³)

Oxidizer: Liquid oxygen

Oxygen

Oxygen is the element with atomic number 8 and represented by the symbol O. Its name derives from the Greek roots ὀξύς and -γενής , because at the time of naming, it was mistakenly thought that all acids required oxygen in their composition...

 (LOX

Lox

Lox is salmon fillet that has been cured. In its most popular form, it is thinly sliced—less than in thickness—and, typically, served on a bagel, often with cream cheese, onion, tomato, cucumber and capers...

) 66,000 US gal (250 m³)

Burn time: 2.5 min

Burnout altitude: 42 miles (67.6 km)

H-1 engine

The H-1

H-1 (rocket engine)

Rocketdyne's H-1 is a thrust liquid-propellant rocket engine burning LOX and RP-1. The H-1 was developed for use in the S-IB first stage of the Saturn I and Saturn IB rockets, where it was used in clusters of eight engines...

 engine is a 200000 lbf (889.6 kN) thrust LOX/RP-1 engine, used alone in the first stages of some Delta rockets and the Jupiter rocket. It is derived from the Navaho missile, and was simplified and improved for S-IB use. It is used in clusters on all S-IB rocket stages. Later it would be uprated to 205000 lbf (911.9 kN) of thrust. The H-1

H-1 (rocket engine)

Rocketdyne's H-1 is a thrust liquid-propellant rocket engine burning LOX and RP-1. The H-1 was developed for use in the S-IB first stage of the Saturn I and Saturn IB rockets, where it was used in clusters of eight engines...

 preceded the F-1 engine

F-1 (rocket engine)

The F-1 is a rocket engine developed by Rocketdyne and used in the Saturn V. Five F-1 engines were used in the S-IC first stage of each Saturn V, which served as the main launch vehicle in the Apollo program. The F-1 is still the most powerful single-chamber liquid-fueled rocket engine ever...

, which was used on the Saturn V rocket.

Fuel: RP-1

RP-1

RP-1 is a highly refined form of kerosene outwardly similar to jet fuel, used as a rocket fuel. Although having a lower specific impulse than liquid hydrogen , RP-1 is cheaper, can be stored at room temperature, is far less of an explosive hazard and is far denser...

 (refined kerosene

Kerosene

Kerosene, sometimes spelled kerosine in scientific and industrial usage, also known as paraffin or paraffin oil in the United Kingdom, Hong Kong, Ireland and South Africa, is a combustible hydrocarbon liquid. The name is derived from Greek keros...

)

Oxidizer: liquid oxygen

Oxygen

Oxygen is the element with atomic number 8 and represented by the symbol O. Its name derives from the Greek roots ὀξύς and -γενής , because at the time of naming, it was mistakenly thought that all acids required oxygen in their composition...

 (LOX

Lox

Lox is salmon fillet that has been cured. In its most popular form, it is thinly sliced—less than in thickness—and, typically, served on a bagel, often with cream cheese, onion, tomato, cucumber and capers...

)

Height: 8.5 ft (2.6 m)

Width: 5.5 ft (1.7 m)

Thrust: 200000 lbf (889.6 kN)

Uprated thrust: 205000 lbf (911.9 kN)

Fuel flowrate: 2092 US gal/min (132 L/s)

Oxidizer flowrate: 3330 gpm (210 L/s)

Oxidizer to fuel ratio: 2.23:1

Type: bipropellant standard

Nominal chamber pressure: 633 psi (4.4 MPa)

Inboard weight: 1780 pounds (807.4 kg)

Outboard weight: 2020 pounds (916.3 kg)

Expansion area ratio: 8:1