A twin-shaft, single-flow turbojet engine with an afterburner. The axial compressor is twin-shaft with three low-pressure and three high-pressure stages. The gas turbine has two stages of high and low pressure. The high-pressure turbine is connected by a shaft to the high-pressure compressor, and the low-pressure turbine to the low-pressure compressor.
The afterburner chamber is terminated by a nozzle regulated by hydraulic actuators. The engine has two bleed ports, at the level of the combustion chambers, for discharging pressurised air to the blown flap system on the wings.
Engine starting is performed by a starter-generator. During engine operation, it functions as a generator powering the aircraft’s onboard electrical equipment and charging the onboard batteries.
This engine is the result of an improvement on the earlier design (R-11F-300) developed at the Mikulin Design Bureau in Moscow, under the direction of designer Tumansky. It was created to meet the need for engines capable of operating at speeds of 2000 km/h. In the 1960s, it was among the most advanced powerplants with excellent operational characteristics. It was produced in large quantities and was used in aircraft: MiG‑21PFM, MiG‑21R, MiG‑21S, MiG‑21M, Su‑15, Yak‑28.
| Maximum thrust | 3950 kG (38.7 kN) |
| Maximum thrust with afterburner | 6120 kG (60 kN) |
| Engine weight | 1194 kg |
| Fuel consumption | 3792 kg/h without afterburner and 14504 kg/h with afterburner |
