V-2 Rocket Engine

Display location: Museum exhibit hall

Fuel: Alcohol - 2,900 liters per rocket
Oxidizer: Liquid oxygen (LOX) - 6,750 kilograms per rocket
Thrust: 25.7 tons (59,500 pounds) at liftoff
Consumption: 72 Kg of LOX and 58 Kg of Alcohol per second at full thrust
Temperature: 2,000 degrees C in combustion chamber
Velocity: Engine exhaust 2,000 meters per second
Weight: 2,053 pounds
Turbo Pump: Hydrogen peroxide and sodium permanganate used to generate steam as power to run the pumps

Related exhibits:

V-2 Jet Vane Motor

The Museum has a rare V-2 rocket engine on display in the Exhibit Hall. Note that the engine is 'upside down' with the nozzle pointing up.

An engine of this type powered a rocket called Bumper on the first launch from Cape Canaveral, 24 July 1950. Bumper was a V-2 with a WAC Corporal second stage.

Fuel lines running to exhaust nozzle. The fuel served to cool the nozzle and prevent it from melting from the extreme heat. Fuel then flowed from the nozzle into the combustion chamber to burn. View the V-2 Engine Fuel System Diagram
Liquid oxygen and fuel lines at the base of the combustion chamber.	Turbo-pumps for fuel and liquid oxygen with their associated tubing.