NK-9

Manufacturer Name: NK-9. Designer: Kuznetsov. Developed in: 1959-65. Application: R-9, GR-1 stage 1. Propellants: Lox/Kerosene. Thrust(vac): 441.300 kN (99,208 lbf). Thrust(sl): 360.390 kN (81,019 lbf). Isp: 327 sec. Isp (sea level): 280 sec. Chambers: 1. Country: Russia. First Flight: 1965.

Developed for 1st Stage of the R-9 ICBM, reached phase of stand testing, but then RD-111 selected. Later planned for 1st Stage of GR-1, but that rocket was abandoned. OKB Kuznetsov.

NK-9 used on Rocket Stages

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

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

Bibliography and Further Reading

Vetrov, G S, S. P. Korolev i evo delo, Nauka, Moscow, 1998. ISBN: 5020036846. The collected papers of Soviet Chief Designer Korolev. A tremendous source of new information and insight on the Soviet space program. Russian language. More at amazon.com...

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

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.

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