Rocket Engine, Liquid Fuel, S-3D for Jupiter Missile

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    Rocket Engine, Liquid Fuel, S-3D for Jupiter Missile

    Tubular at top of combustion chamber with large bell-shaped nozzle flaring out below and pumps and other plumbing joined to the top of the chamber and thrust mounting. The engine also features regenerative-cooling through the "spaghetti" configuration in which the cooling tubes form the longitudinal walls of the chamber thereby both strengthening the chamber as well as cooling it with the flow of fuel prior to injection. A series of horizontal bands further strengthen the chamber. Torn fabric around, impeller ring bent, and rust in many areas.

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Display Status:

This object is not on display at the National Air and Space Museum. It is either on loan or in storage.

Developed in the 1950s, the S-3 D Jupiter engine powered the U.S.'s first intermediate range (1600 miles) ballistic missile (IRBM). A modification of the Redstone engine, the Jupiter engine, which operated on liquid oxygen and RP-1 (a type of kerosene), produced 150,000 lbs of thrust for 178 seconds. The Jupiter missile itself was 58 feet (17.7 m) long, 8.75 feet (2.7 m) in diameter, and weighed 110,000 lbs (49,900 kg).

NASA transferred this engine to the Museum in 1969.