Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z
LR19
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.

AKA: XLR19-CW-1. Thrust: 44.10 kN (9,914 lbf). Unfuelled mass: 268 kg (590 lb). Burn time: 120 s. Height: 3.35 m (10.99 ft). Diameter: 0.81 m (2.65 ft).

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.

Country: USA. Propellants: Lox/Gasoline. Agency: Curtiss-Wright.
Back to top of page
Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z
© 1997-2019 Mark Wade - Contact
© / Conditions for Use