IV»iG 21F13 / Tip 74

The MiG-21 F-13 was the first production MiG-21 armed with K-13 air-to-air missiles, hence its designation. After it was accepted by the air force, the K-13 was renamed R-3.

and the bracket for the gear leg hinge was placed at the juncture of those two spars

3. A rear spar preceded by ten ribs that were set parallel to the fuse­lage datum line, and a rear false spar

The rear wet wing tanks were located between rib nos. 1 and 6. The upper and lower walls of the fuel tanks were made of machined plates of the V-95 alloy, the same one used for skin panels without stiff­eners. The wing was attached to the fuselage by five fittings, three to transmit the moment (matched with the front, center, and rear spars) and two to convey the bending strain (matched with the front and rear false spars). The all-metal semimonocoque fuselage could be split into two parts between frame nos. 28 and 28A (twenty-eight frames in front, thirteen to the rear). Other basic components included body longerons in front, stringers at the rear, and relatively thick skin to strengthen the whole structure. The air intake, like that of the MiG-21F, housed a three-position cone that controlled the duct area according to the air­craft’s speed: up to Mach 1.5 the cone did not move, between Mach 1.5 and 1.9 it moved forward partway, and beyond Mach 1.9 it moved far­ther forward.

This MiG-21F 13 is equipped with a finned ‘supersonic” drop tank having a capacity of 4901 (129 US gallons).

The side airbrakes hinged to frame no 11, each measured 0.38 m2 (4 1 square feet) and had a maximum deflection of 25 degrees, the belly airbrake measured 0 47 nT (5 06 square feet) and had a maximum deflection of 40 degrees Under the tail section of the fuselage was a ventral fin 0 352 m (13 85 inches) high with a canister for a 16-mz (172 2-square foot) tail chute on its left When the chute was deployed the landing roll was cut by about 400 m (1,310 feet) The engine bay was located between frame nos 29 and 34 The cockpit was pressur­ized and air-conditioned, a special regulator kept the temperature in the 15° C range give or take 5° C

The fuselage had maximum diameter of 1 242 m (4 feet, 0.9 inch­es) and a maximum cross-section of 1 28 m2 (13 8 square feet) The tail fin had a sweepback of 60 degrees at the leading edge and an area of 3 8 m2 (40 9 square feet), versus 4 08 m2 (43.9 square feet) for the MiG- 21F and the first 114 MiG-21F-13s, the rudder had an area of 0 965 m2 (10 4 square feet) and a maximum deflection of plus-or-mmus 25 degrees, tail fin airfoil, TsAGI S-ll; thickness/chord ratio, 6 percent. The stabilator had a 55-degree sweepback at the leading edge, an area of 3 94 m2 (42 4 square feet), a span of 3 74 m (12 feet, 3 2 inches), no dihedral, an A6A symmetrical airfoil, and a thickness/’chord ratio of 6 percent This all-flymg tail had a variable incidence ranging from +7 5 to -16 5 degrees and the ARU-3V feel computer

The tricycle landing gear was composed of a forward nosewheel unit (tire size 500 x 180) that retracted forward between frame nos. 6 and 11 and a main wheel unit that retracted inward. The gear legs lodged in the wing, but the wheels (660 x 200) turned themselves 87 degrees to stow vertically inside the fuselage. The gear was hydraulical­ly controlled and had a backup pneumatic system.

The cockpit was fitted with the SK ejection seat, a system that used the canopy to protect the pilot. The instrument panel included (besides the basic instrumentation) the KAP-2K autopilot with roll limitation of plus-or-minus 35 degrees, the R-802V (RSIU-5V) VHF, the MRP-56P marker receiver, the ARK-10 automatic direction finder, the RV-UM radio-altimeter for 0-600 m (0-1,970 feet), the SOD-57M decimetric transponder, the Sirena 2 radar warning receiver, and the SRO-2 IFF transponder.

The R-11F-300 turbojet was rated at 3,820 daN (3,900 kg st) dry and from 4,800 daN (4,900 kg st) to 5,625 daN (5,740 kg st) with a throt­tleable afterburner. The fuel tank capacity—2,280 1 (602 US gallons) in the aircraft’s first series—was increased to 2,550 1 (673 US gallons). The MiG-21 F-13 could also carry a drop tank under the fuselage with 490 or 8001 (129 or 211 US gallons) of fuel.

Armament consisted of a single NR-30 cannon with thirty rounds on the right side of the fuselage and either two R-3S air-to-air missiles (IR seeker, firing distance of 1 to 7 km [0.62 to 4.3 miles]), two UB-32- 57U rocket pods (S-5 rockets), two 240-mm S-24 rockets, or two bombs (up to 500 kg [1,100 pounds] apiece) on two underwing pylons. The ASP-5ND gunsight was linked to the SRD-5M Kvant ("quantum”) rang­ing radar. For limited reconnaissance missions the aircraft could be equipped with the AFA-39 camera.

The MiG-21 F-13 was mass-produced in the Gorki factory between 1960 and 1962 for the WS and in the MMZ Znamya Truda factory in Moscow between 1962 and 1965 for export.

Specifications

Span, 7.154 m (23 ft 5.7 in), length (except probe), 13.46 m (44 ft 1.9 in); overall length, 15.76 m (51 ft 8 5 in), height, 4.1 m (13 ft 5.4 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); empty weight, 4,980 kg (10,975 lb); take­off weight with two R-3S missiles, 7,370 kg (16,245 lb); max takeoff weight with 490-1 (129-US gal) drop tank and two 500-kg (1,100-lb) bombs, 8,625 kg (19,010 lb); fuel, 2,115 kg (4,660 lb); wing loading, 320.4-375 kg/m2 (65.7-76.9 lb/sq ft); max operating limit load factor, 7.

Performance

Max speed, 2,175 km/h at 13,000 m (1,175 kt at 42,640 ft); max speed at sea level, 1,150 km/h (621 kt); climb rate at sea level in clean con­figuration, 175 m/sec (34,450 ft/min); climb to 19,000 m (62,300 ft)

The Ye-6V/1 (as well as the Ye-6V/2) was used to test various devices for short takeoff and landing. The canister for the brake chute is located at the base of the fin.

This Ye-6V/2 is equipped with a finned drop tank, two K-13 air-to-air missiles, and two JATO boosters.

On 9 July 1961 Fedotov executed a jet-assisted takeoff in public in the Ye-6V/2.

with 490-1 (129-US gal) drop tank and two R-3S missiles in 13.5 min; service ceiling, 19,000 m (62,300 ft); landing speed, 280 km/h (151 kt); range, 1,300 km at 11,000 m (810 mi at 36,080 ft); with 800-1 (211-US gal) drop tank, 1,670 km (1,040 mi); takeoff roll, 800 m (2,625 ft); land­ing roll with tail chute, 800 m (2,625 ft).