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RD-252


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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
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