MiG21PF / Tip 76 / Yb-7G

If the MiG-21P descended from the MiG-21F, the MiG-21PF descended from the MiG-21F-13. However, it contained the more powerful R-11F-

300, rated at 3,870 daN (3,950 kg st) or 6,000 daN (6,120 kg st) with afterburner. The greater volume of the nose cone (which housed a big­ger radar unit) and the increased airflow essential for the new turbojet meant that the diameter of the air intake had to be increased from 690 mm (27.2 inches) to 870 mm (34.25 inches). It is noteworthy that this change had already taken place on the MiG-21 P.

A new system, the UVD-2M, was developed to ensure steady con­trol of the nose cone at all flight regimes. (On the ground, the cone extended 1,213 mm [47.8 inches] ahead of the air intake plane; in flight, according to speed, this could be reduced to 200 mm [7 9 inches].) This MiG-21PF inherited such modifications from the MiG-21P as larger wheels and attachment points for solid propellant boosters. However, its silhouette was somewhat modified by the removal of the rear win­dow in the canopy and the new shape of the dorsal fairing immediately behind the cockpit; this housed two more fuel tanks, bringing the total fuel capacity to 2,750 1 (726 US gallons). In addition, the PDV-5 air data probe—which on earlier versions was set axially under the air intake— was moved above and to the right of the intake.

The RP-21 Sapfir ("sapphire’’) radar made its debut on the MiG – 21PF. The ASP-5ND gunsight was replaced by a PKI-1. Other equip­ment included the KAP-2 autopilot (still only for roll stabilization), a guidance command receiver, and an IFF interrogator. Like the MiG – 21 P, the PF had no cannon. Its armament was limited to two K-13 air – to-air missiles that could be replaced by the usual weaponry options

(rocket pods, bombs, etc.). On PF late series the tail chute canister was set at the base of the tail fin, a position that was tried out on the Ye-6V.

In early 1962 a decree signed by the minister of defense accepted the MiG-21 PF into the military inventory of the USSR. The aircraft was mass-produced in the Gorki factory between 1962 and 1964 for the WS and in the MMZ Znamya Truda factory in Moscow between 1964 and 1968 for export. A MiG-21 PF—renamed Ye-76 for this purpose—broke several female world records in 1966 and 1967:

1. 16 September 1966. Speed over a closed circuit of 500 km (310 miles), 2,062 km/h (1,113.5 kt). Pilot, M. Solovyeva

2. 11 October 1966. Speed over a closed circuit of 2,000 km (1,240 miles), 900 267 km/h (559.07 kt). Pilot, Ye. Martova

3. 18 February 1967. Speed over a closed circuit of 100 km (62 miles), 2,128.7 km/h (1,149.5 kt). Pilot, Ye. Martova

4. 28 March 1967. Speed over a closed circuit of 1,000 km (620 miles), 1,928.16 km/h (1,041.2 kt). Pilot, L. Zaitseva

The documents sent to the FAI mentioned that the Ye-76 was pow­ered by an R-37F turbojet rated at 5,830 daN (5,950 kg st).

Specifications

Span, 7 154 m (23 ft 5.7 in); fuselage length (except cone), 12 285 m (40 ft 3.7 in); wheel track, 2.692 m (8 ft 10 in); wheel base, 4 806 m (15 ft 9.2 in); wing area, 23 m2 (247.6 sq ft); takeoff weight, 7,750 kg (17,080 lb); max takeoff weight, 9,500 kg (20,940 lb); max takeoff weight on rough strip or metal-plank strip, 8,800 kg (19,395 lb); fuel, 2,280 kg (5,025 lb); wing loading, 337-413-382.6 kg/m2 (69.1-84.7-78.4 lb/sq ft); max operating limit load factor, 8.

Performance

Max speed, 2,175 km/h at 13,000 m (1,175 kt at 42,640 ft); max speed at sea level, 1,300 km/h (702 kt); climb to 18,500 m (60,700 ft) in 8 min; service ceiling, 19,000 m (62,300 ft); climb rate at sea level (half internal fuel, full thrust) with two R-3S missiles, 205 m/sec (40,350 ft/min); landing speed, 280 km/h (151 kt); range, 1,400 km (870 mi); with 800-1 (211-US gal) drop tank, 1,770 km (1,100 mi); takeoff roll, 850 m (2,790 ft); landing roll with tail chute, 850 m (2,790 ft).