XLR24AJ-2

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XLR24AJ-2

Aerojet Nitric acid/Gasoline rocket engine. Development begun January 1946. Blast turbine, 2500 lbf fixed thrust (both were part of overall R&D contract)

AKA: XLR24-AJ-2. Date: January 1946. Thrust: 10.70 kN (2,405 lbf).

Thrust (sl): 10.700 kN (2,405 lbf). Thrust (sl): 1,100 kgf. Propellant Formulation: WFNA/Gasoline.

Family: Storable liquid. Country: USA. Launch Vehicles: Lark. Propellants: Nitric acid/Gasoline. Agency: Aerojet.

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