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The sign accompanying the engine. It reads

U.S. Army Redstone Rocket Engine

This engine powered the Redstone rocket. It was actually modified from an earlier engine developed by North American Aviation for the Navaho cruise missile. This liquid-propellant engine utilized a turbopump. The turbine was driven by hot gases generated from hydrogen peroxide, which was stored in the red tank above the engine. The gases were then exhausted through the duct on the side. Total burn time was 121 seconds (about 2 minutes). Note also, that several metal joints are shaped to resemble an accordion or "bellows" shape. These served to reduce strain during operation.

Thrust:	75,000 lbs (334,000N), missile version (Redstone) 78,000 lbs (347,000N), manned version (Mercury-Redstone) 83,000 lbs (369,000N), satellite version (Jupiter-C)
Propellant:	liquid oxygen and ethyl alcohol, missile version (Redstone) liquid oxygen and ethyl alcohol, missile version (Mercury-Redstone) liquid oxygen and hydyne, satellite version (Jupiter-C)

Contractors: Rocketdyne Div., North American Aviation, Inc.