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NK-9V
Part of NK-9
Kuznetsov LOx/Kerosene rocket engine. N-1 stage 2 / N-1 stage 3 / R-9 Stage 2. Developed for 2nd stage of the R-9 ICBM (alternative to RD-111 engine by OKB-456). NK-9 with increased expansion ratio. First flight 1965.

AKA: 11D53;NK-19;NK-19, NK-21;NK-21. Date: 1959-65. Thrust: 441.30 kN (99,208 lbf). Specific impulse: 340 s. Specific impulse sea level: 312 s.

Thrust (sl): 360.390 kN (81,019 lbf). Thrust (sl): 36,750 kgf. Propellant Formulation: Lox/RG-1.

Country: Russia. Launch Vehicles: R-9A. Propellants: Lox/Kerosene. Stages: 8K513 Blok B. Agency: Kuznetsov bureau.
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