NK-33

NK-33
Credit - Karl Dodenhoff

Manufacturer Name: NK-33. Government Designation: 11D111. Designer: Kuznetsov. Developed in: 1970-74. Application: N-1F stage 1 (block A). Propellants: Lox/Kerosene. Thrust(vac): 1,638.000 kN (368,237 lbf). Thrust(sl): 1,510.200 kN (339,506 lbf). Isp: 331 sec. Isp (sea level): 297 sec. Burn time: 600 sec. Mass Engine: 1,222 kg (2,694 lb). Diameter: 1.50 m (4.90 ft). Length: 3.71 m (12.17 ft). Chambers: 1. Chamber Pressure: 145.70 bar. Area Ratio: 27.00. Oxidizer to Fuel Ratio: 2.80. Thrust to Weight Ratio: 136.66. Country: Russia. Status: Design 1975.

After initial failures of N1 modified engines with multiple ignition capability and increased life were developed. NK-33 was tested at thrust of up to 204 t, variations of components ratio up to 20% and total burning time up to 1200 sec. Mothballed, never flown until selected by Kistler for their commercial launch vehicle in 1996.

NK-33 used on Rocket Stages

Used on stage: Kistler Stage 1. on launch vehicle: Kistler K-1.

Used on stage: N1F Block A. on launch vehicle: N1F.

Used on stage: N1F Block A. on launch vehicle: N1F Sr.

Used on stage: N1F Block A. on launch vehicle: N1F-L3M.

Used on stage: UR-500MK-1. on launch vehicle: UR-500MK.

Bibliography and Further Reading

Data sheets NPO Trud 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 - 2007 except where otherwise noted.

Encyclopedia Astronautica
topic index
0 - A - B - C - D - E - F - G - H - I - J - K - L - M - N - O - P - Q - Ra - Re - Sa - Sf - Sp - T - U - V - W - X - Y - Z