MiG 2011/lift 50

The MiG-21SMT frontline fighter-interceptor was a cross between the MiG-21M (same airframe, same armament) and the MiG-21MT (same R-13F-300 turbojet, same fuel capacity). The new engine led to modifi­cations of the fuel system and a new setting of the cone control pro­gram. The VHF/UHF communications equipment was improved. The huge dorsal tank proved to be the cause of a major and unfortunate drawback: the aircraft’s yaw stability margin had deteriorated. The capacity of the tank had to be reduced from 900 1 (238 US gallons) to 6001 (159 US gallons), cutting the aircraft’s total fuel capacity to 2,9501 (779 US gallons). The MiG-21SMT’s radar was the RP-22 Sapfir-21, and its armament included a built-in GSh-23L, R-3S/R-3R air-to-air missiles (or R-60/R-60Ms for close combat), and/or UB-16 and UB-32 rocket pods, 240-mm S-24 rockets, and bombs.

The MiG-21SMT was mass-produced in the Gorki factory between 1971 and 1972.

Specifications

Span, 7.154 m (23 ft 5.7 in); fuselage length (except cone), 12.285 m (40 ft 3.7 in); wheel track, 2.787 m (9 ft 1.7 in); wheel base, 4.71 m (15 ft 5.4 in); wing area, 23 m2 (247.6 sq ft); takeoff weight, 8,900 kg (19,615 lb); max takeoff weight, 9,100 kg (20,055 lb); max takeoff weight on rough strip or metal-plank strip, 8,800 kg (19,385 lb); fuel, 2,450 kg (5,400 lb); wing loading, 387-395.7-382.6 kg/m2 (79.3-81.1-78.4 lb/sq ft); max operating limit load factor, 8.5.

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 rate at sea level (half internal fuel, full thrust) with two R-3S missiles, 200 m/sec (39,370 ft/min), climb to 16,800 m (55,100 ft) in 9 min; service ceiling, 17,300 m (56,745 ft); landing speed, 250 km/h (135 kt); range, 1,300 km (810 mi); with 800-1 (211-US gal) drop tank, 1,670 km (1,035 mi); takeoff roll, 950 m (3,115 ft); landing roll with SPS and tail chute, 550 m (1,800 ft).