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
X45ALD-4000
Part of 40AL Family
Aerojet Nitric acid/Amine rocket engine. Development begun June 1948. Regenerative cooling, nitrogen pressure-fed, droppable but no recoverable. Early version using XLR-13-AJ-1 thrust chamber assembly.

AKA: XLR13-AJ-3. Date: June 1948. Thrust: 17.60 kN (3,957 lbf). Unfuelled mass: 403 kg (888 lb). Burn time: 60 s. Height: 4.50 m (14.70 ft). Diameter: 0.94 m (3.08 ft).

Thrust (sl): 17.600 kN (3,957 lbf). Thrust (sl): 1,800 kgf. Engine: 403 kg (888 lb). Chamber Pressure: 21.40 bar. Propellant Formulation: RFNA/70% Xylidine+30% AN-F-48.



Family: Storable liquid. Country: USA. Propellants: Nitric acid/Amine. Agency: Aerojet.

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