The engine was developed at the Archip Lyulka design bureau in the late 1960s. It is used in the MiG-23B, Su-17, Su-20, Su-22 and Su-24 combat aircraft.
| Configuration | single-shaft single-flow turbojet engine with 14-stage compressor, annular-tubular combustion chamber, 3-stage turbine and afterburner |
| Weight | 1720 kg |
| Maximum thrust without afterburner | 78 kN (7953 kG) |
| Maximum thrust with afterburner | 111.5 kN (11369 kG) |
