Usage Conditions May Apply Usage Conditions Apply There are restrictions for re-using this media. For more information, visit the Smithsonian's Terms of Use page. IIIF provides researchers rich metadata and image viewing options for comparison of works across cultural heritage collections. More - https://iiif.si.edu View Manifest View in Mirador Viewer Usage Conditions May Apply Usage Conditions Apply There are restrictions for re-using this media. For more information, visit the Smithsonian's Terms of Use page. IIIF provides researchers rich metadata and image viewing options for comparison of works across cultural heritage collections. More - https://iiif.si.edu View Manifest View in Mirador Viewer Usage Conditions May Apply Usage Conditions Apply There are restrictions for re-using this media. For more information, visit the Smithsonian's Terms of Use page. IIIF provides researchers rich metadata and image viewing options for comparison of works across cultural heritage collections. More - https://iiif.si.edu View Manifest View in Mirador Viewer Usage Conditions May Apply Usage Conditions Apply There are restrictions for re-using this media. For more information, visit the Smithsonian's Terms of Use page. IIIF provides researchers rich metadata and image viewing options for comparison of works across cultural heritage collections. More - https://iiif.si.edu View Manifest View in Mirador Viewer

This is the F-1 rocket engine used in the first stage of the Saturn V launch vehicle, which launched astronauts to the Moon in the Project Apollo program. The first, or S-IC stage, of the Saturn V, was fitted with five F-1s for a total lift-off thrust of 7.5 million pounds. The fully-fueled Saturn V weighed 6.5 million pounds.

The F-1 used RP-1, a type of kerosene, and liquid oxygen as the propellants. The F-1's 2,500 pound turbopump pumped in the propellants at 42,500 gallons per minute. The engine was regeneratively-cooled.

This engine was donated by Rocketdyne Division, Rockwell International.

 Display Status

This object is not on display at the National Air and Space Museum. It is either on loan or in storage.
Object Details
Country of Origin United States of America Type PROPULSION-Rocket Engines Manufacturer Rocketdyne Division, Rockwell International
 Dimensions Overall: 196 long x 54 in. diameter (497.84 x 137.16cm)
Other: 131 in. wide (332.74cm)
 Materials Cooling tubes (178 tubes), Inconel X; injector, stainless steel and copper; propellant lines, aluminum; valves, aluminum and stainless steel
 Inventory Number A19760765000 Credit Line Gift of Rocketdyne Division, Rockwell International Data Source National Air and Space Museum Restrictions & Rights Usage conditions apply
For more information, visit the Smithsonians Terms of Use.