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 a J-2 liquid propellant rocket engine that uses liquid hydrogen and liquid oxygen. It was the powerplant for the second and third stages of the Project Apollo Saturn V launch vehicle which took astronauts to the Moon. The J-2 had a thrust of about 200,000 pounds but was later upgraded to 250,000 pounds. The J-2 shown here is an early development model and was used in three test firings for a total firing duration of 291 seconds. The Saturn V's second stage used five J-2's for a combined thrust of 1,150,000 pounds while the third stage had a single J-2. This engine was transferred by to the Smithsonian in 1986 from the NASA Marshall Space Flight Center.

 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 Pratt & Whitney
 Dimensions Overall: 132 in.long x 78 in. diameter, 5000 lb. (335.28cm, 2268kg, 198.12cm)
 Materials Stainless steels and other metals
 Inventory Number A19940099000 Credit Line Transferred from the National Aeronautics and Space Administration Data Source National Air and Space Museum Restrictions & Rights Usage conditions apply
For more information, visit the Smithsonians Terms of Use.