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The alcohol inlet.

The thrust chamber assembly was double-walled; the alcohol fuel entered through this inlet, near the engine's exit plane, and flowed between the two walls toward the injector at the forward end of the engine, providing regenerative cooling.

Two versions of the Redstone engine were installed in production missiles, the A-6 and the A-7. The most obvious difference between the two is that the A-6 had two alcohol inlets, located 180° apart.