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
LR17
Curtiss-Wright LOx/Gasoline rocket engine. Assisted take-off power for XB-45. Single thrust chamber, both regeneratively cooled and film-cooled with water, spark plug ignition, turbine-pump fed.

AKA: XLR17-CW-1. Thrust: 17.60 kN (3,957 lbf). Unfuelled mass: 268 kg (590 lb). Burn time: 60 s. Height: 3.35 m (10.99 ft). Diameter: 0.81 m (2.65 ft).

Dropped by parachute. Similar in performance to Aerojet AJ-13.

Thrust (sl): 17.600 kN (3,957 lbf). Thrust (sl): 1,800 kgf. Engine: 268 kg (590 lb). Chamber Pressure: 20.00 bar. Propellant Formulation: Lox/Low octane gasoline+coolant water.



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