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MiG-21 Lancer

MiG-21 was designed as a clear-weather interceptor and the prototype flew for the first time in 1957. The aircraft entered mass production in 1958 powered by a Tumanski R-11 turbojet, but reached its definitive form in the following year with the MiG-21F, with an engine uprated to 56.39 kN. This paved the way for the MiG-21PF of 1960, with the uprated R-11F engine and an enlarged inlet to allow the incorporation of R-1L radar in the centrebody, the MiG-21PFS, with blown flaps and a ventral pod carrying a 23mm GSh-23L two-barrel cannon, and the MiG-21PFM, incorporating all the sequential improvements of earlier models. The second generation MiG-21MF featured additional fuel, RP-21
The aircraft is equipped with a KM-1M ejection seat, that provides escape capability for the pilot at 0 m altitude and a minimum sped of 130 km/h.

Technical data

Powerplant: Tumanskii R-13-300 turbojet engine, 68 kN or Tumanskii R-11F2S-300, 63 kN.
- Length: 14,5m;
- Height: 4,1m;
- Wingspan: 7,15m.
- Normal take-off weight: 5750 kg;
- Maximum take-off weight: 10400kg.
- GS-23L two-barrel 23-mm caliber gun;
- 1000 kg external stores including air-to-air missiles (R-3S, R-13M, R-60M, R-73, Python 3, Magic 2); air to ground S-24 rockets; rocket pods, conventional and smart bombs, external fuel tanks, laser designation pod, photo reconnaissance or jamming pods attached to 5 hardpoints.
Crew: 1 (2 for MiG-21 Lancer B).
Payload: 200kg.
- Maximum speed at 10000m: 2175km/h (Mach 2,1);
- Maximum speed at sea level: 1300km/h (Mach 1,1);
- Ceiling: 18000 m;
- Maximum range: 1500 km.
MiG-21 Lancer A
MiG-21 Lancer A
MiG-21 Lancer B
MiG-21 Lancer B
MiG-21 Lancer C
MiG-21 Lancer C
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