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LR21
Curtiss-Wright LOx/Gasoline rocket engine. Turbine pump-fed, single thrust chamber unit intended for cancelled missile application. Engine designed to fit into the envelope dimensions of the German V-2!

AKA: XLR21-CW-1. Thrust: 266.83 kN (59,986 lbf). Unfuelled mass: 147 kg (324 lb). Burn time: 120 s.

Regeneratively cooled and film cooled with water-alcohol mixture, spark plug ignition.

Thrust (sl): 266.830 kN (59,986 lbf). Thrust (sl): 27,210 kgf. Engine: 147 kg (324 lb). Propellant Formulation: Lox/Low octane gasoline+coolant water+alcohol.

Country: USA. Propellants: Lox/Gasoline. Agency: Curtiss-Wright.
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