RD-113 home
topic index
Engine Model: RD-113. Manufacturer Name: RD-113. Designer: Glushko. Developed in: 1960. Application: ICBM stage 2 (stage 1 was RD-112). Propellants: Lox/UDMH. Thrust(vac): 1,138.000 kN (255,832 lbf). Isp: 360 sec. Mass Engine: 1,100 kg (2,400 lb). Diameter: 2.48 m (8.13 ft). Length: 4.20 m (13.70 ft). Chambers: 1. Chamber Pressure: 147.00 bar. Area Ratio: 119.80. Oxidizer to Fuel Ratio: 1.70. Thrust to Weight Ratio: 105.49. Country: Russia. Status: Developed 1960.

Upper stage version of RD-112 with larger nozzle.

Bibliography:

  • Glushko, V P, Albom Konstruktsiy ZhRD, Vol. 1 1968, Vol. 3 & 4 1969 via Dietrich Haeseler.
Contact us with any corrections, additions, or comments.
Conditions for use of drawings, pictures, or other materials from this site..
To contact astronauts or cosmonauts.

© Mark Wade, 1997 - 2008 except where otherwise noted.