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
X60ALD-4000
Part of 40AL Family
Aerojet Nitric acid/Amine rocket engine. ATO for XB-45, B-45A. Development begun May 1946. Pressurizing tank surrounded propellant tanks. Regeneratively cooled. Parachute for dropping and recovery after takeoff.

AKA: XLR13-AJ-1. Date: May 1946. Thrust: 17.60 kN (3,957 lbf). Unfuelled mass: 363 kg (800 lb). Burn time: 60 s. Height: 3.43 m (11.25 ft). Diameter: 0.81 m (2.65 ft).

Later redesigned to use WFNA and gasoline.

Thrust (sl): 17.600 kN (3,957 lbf). Thrust (sl): 1,800 kgf. Engine: 363 kg (800 lb). Chamber Pressure: 21.00 bar. Propellant Formulation: RFNA/80% Aniline+20% Furfural Alcohol.



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