Aircraft engine: Tumansky R-11F2SK-300
|Maximum dry thrust||3,950 kG (8,708 lbf, 38.7 kN)|
|Maximum thrust with afterburner||6,120 kG (13,492 lbf, 60 kN)|
|Mass||1,194 kg (2,632 lb)|
|Fuel consumption||3792 kg/h without afterburner and 14 504 kg/h with afterburner|
Twin-spool axial flow turbojet engine with afterburner. The axial compressor is a twin-spool one with three stages of high and three stages of low pressure. The gas turbine has low and high pressure stage. The high pressure turbine is connected by a shaft with high pressure compressor and the low pressure turbine is connected with low pressure compressor. The afterburner chamber ends with a nozzle of diameter regulated by hydraulic actuators. The engine has two openings near the combustion chamber providing bleed air to the blown flaps installation.
The engine is started by generator-starter which during the flight supplies power to aircraft’s systems and charges batteries.
The engine is a development version of the previous design (R11 F-300) of the Mikulin Design Bureau of Moscow under the supervision of S. Tumansky. It was developed in order to meet Soviet Air Force’s requirement for an engine able to run at speeds exceeding 2,000 km/h. In 1960s it was a very modern powerplant with good handling qualities. It was manufactured in large numbers and used in MiG‑21PFM, MiG-21R, MiG‑21S, MiG‑21M, Su‑15 and Yak‑28 aircraft.