LR19
Engine · USA
Original archive entry. The text, images and links below are kept as they were written.
Curtiss-Wright LOx/Gasoline rocket engine. Experimental unit for either missiles or piloted aircraft. Single thrust chamber, regeneratively cooled and film cooled with water-alcohol mixture.
Turbo-pump with sufficient capacity to reach 7300 kgf.
Thrust (sl): 44.100 kN (9,914 lbf). Thrust (sl): 4,500 kgf. Engine: 268 kg (590 lb). Chamber Pressure: 25.50 bar. Propellant Formulation: Lox/Low octane gasoline+coolant water+alcohol.
Related
- Country
- USA
- Propellants
- Lox/Gasoline
- Agency
- Curtiss-Wright