A single-flow, single-shaft turbojet engine with a nine-stage axial compressor. It features a system controlling air bleed from the fifth compressor stage depending on its compression ratio. From the compressor, the air flows to ten combustion chambers housed in a common casing.
The two-stage axial gas turbine is followed by an afterburner chamber with a hydraulically regulated nozzle. The engine was developed in the early 1950s at the Mikulin Design Bureau as a lightweight, high-thrust powerplant for fighter aircraft.
It was also produced in the People’s Republic of China. It was used in the MiG-19S, MiG-19P, MiG-19PM and Yak-25 aircraft.
| Maximum thrust without afterburner | 2600 kG |
| Maximum thrust with afterburner | 3250 kG |
| Cruising thrust | 1750 kG |
| Fuel consumption | 1470 kg/h at cruising thrust |
