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
LR89-5
Part of LR79 Family
B2C/MA-1/MA-2
B2C/MA-1/MA-2
Credit: Boeing / Rocketdyne
Rocketdyne LOx/Kerosene rocket engine. Atlas E, F. Designed for booster applications. Gas generator, pump-fed. Separate turbopumps for each booster engine. First flight 1960.

Date: 1958. Number: 504 . Thrust: 822.50 kN (184,905 lbf). Specific impulse: 290 s. Specific impulse sea level: 256 s. Burn time: 120 s. Height: 3.40 m (11.10 ft). Diameter: 1.53 m (5.00 ft).

Thrust (sl): 726.000 kN (163,211 lbf). Thrust (sl): 74,037 kgf. Engine: 720 kg (1,580 lb). Chamber Pressure: 41.00 bar. Area Ratio: 8. Propellant Formulation: Lox/RP-1. Thrust to Weight Ratio: 116.486111111111. Oxidizer to Fuel Ratio: 2.25. Coefficient of Thrust vacuum: 1.42466495026104. Coefficient of Thrust sea level: 1.22954299904152.



Country: USA. Spacecraft: Ames Mach 10 Demonstrator. Launch Vehicles: Atlas Centaur LV-3C, Atlas E, Saturn B-1, Atlas Agena B, Atlas F, Atlas Agena D, Atlas SLV-3. Propellants: Lox/Kerosene. Stages: Titan Cluster, Atlas MA-3. Agency: Rocketdyne.

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