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
RD-0124M
Part of RD-0106 Family
Kosberg LOx/Kerosene rocket engine. Developed 1998-. Proposed single chamber variant of RD-0124. Obviously same turbopumps, but one single chamber.

Status: Developed 1998-. Date: 1998-. Thrust: 294.30 kN (66,161 lbf). Unfuelled mass: 360 kg (790 lb). Specific impulse: 348 s. Burn time: 300 s. Height: 2.10 m (6.80 ft). Diameter: 1.43 m (4.69 ft).

Engine: 360 kg (790 lb). Chamber Pressure: 161.90 bar. Thrust to Weight Ratio: 83.33.



Country: Russia. Propellants: Lox/Kerosene. Agency: Kosberg bureau.

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