NK-9V

Manufacturer Name: NK-9V. Government Designation: 11D53. Other Designations: NK-19, NK-21. Designer: Kuznetsov. Developed in: 1959-65. Application: N-1 stage 2 (block V) / N-1 stage 3 (block G) / R-9 Stage 2. Propellants: Lox/Kerosene. Thrust(vac): 441.300 kN (99,208 lbf). Thrust(sl): 360.390 kN (81,019 lbf). Isp: 340 sec. Isp (sea level): 312 sec. Chambers: 1. Country: Russia. First Flight: 1965.

Developed for 2nd stage of the R-9 ICBM (alternative to RD-111 engine by OKB-456). NK-9 with increased expansion ratio.

NK-9V used on Rocket Stages

Used on stage: GR-1 Stage 2. on launch vehicle: GR-1.

Bibliography and Further Reading

Anisimov, V S; Lacefield, T C; Andrews, J, AIAA Joint Propulsion Conference, "Evolution of the NK-33 and NK-43 reusable LOX/kerosene engines", via Dietrich Haeseler.

Russian Space Industry, Federation of American Scentists Web Pages, 1998 via Dietrich Haeseler. Accessed at: http://www.fas.org/spp/civil/russia/.

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