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
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.

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
© 1997-2017 Mark Wade - Contact
© / Conditions for Use