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-252
Part of RD-215
RD-252 NPO Enerogmash Museum, November 1992 Credit: © Dietrich Haeseler |
Glushko N2O4/UDMH rocket engine. R-36-0 stage 2; Tsyklon 2 stage 2. In production. Used modified chamber from RD-219, nozzle is conventional, so performance is higher. First flight 1965.
Status: In production. Date: 1961-66. Number: 131 . Thrust: 940.50 kN (211,433 lbf). Unfuelled mass: 715 kg (1,576 lb). Specific impulse: 317 s. Burn time: 160 s. Height: 2.19 m (7.17 ft). Diameter: 2.59 m (8.49 ft).
Chambers: 2. Engine: 715 kg (1,576 lb). Chamber Pressure: 89.50 bar. Area Ratio: 46.1. Thrust to Weight Ratio: 134.12. Oxidizer to Fuel Ratio: 2.6.
Family:
Storable liquid.
Country:
Russia.
Launch Vehicles:
R-36O 8K69,
Tsiklon-2.
Propellants:
N2O4/UDMH.
Stages:
R-36-2,
R-36-0-2,
Tsyklon 2-2.
Agency:
Glushko bureau.
Bibliography:
317,
342,
349.
Back to top of page
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
© 1997-2019 Mark Wade - Contact
© / Conditions for Use