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.