1-380 /1-3

The 1-3 was a logical follow-on for the 1-1/1-2 design philosophy among various single-engine fighters developed simultaneously with other types such as the MiG-19 that were already being mass-produced Its design and structure were based on standard concepts shared by most other fighters of that time – all-metal structure, highly swept (over 50 degrees) and lift-augmented wing, airbrakes plus tail chute, powerful reheated turbojets, ejection seat, flying controls with artificial feel and gear ratio on the pitch channel, all-purpose on-board systems, and heavy armament (cannons)

The preliminary design of the 1-3 (1-380) frontline fighter, mapped out around the new Klimov VK-3 turbojet, was completed in March 1954 The VK-3 possessed an axial flow compressor, an annular com­bustion chamber, and an afterburner It was rated at 5,615 daN (5,730

kg st) of design nominal thrust and 8,270 daN (8,440 kg st) with after­burner. The I-3’s stabilator and aileron power units were of the irre­versible type. On the other hand, the rudder servo-control units were reversible. The wing had a sweepback of 60 degrees С/4. The airbrakes covered an area of 1.2 m2 (12.9 square feet) and flanked the fuselage just behind the wing root. Their role was not only to shorten the land­ing roll and to improve the aircraft’s handling in level flight but also to reduce the aircraft’s speed during a full-power vertical dive. The PT 2165-511 tail chute was 15 m2 (161.5 square feet) in area. Armament consisted of three NR-30 cannons, two on the right and one on the left in the leading edge near the wing root. The pilot was protected by a 65- mm-tbick bulletproof windshield, a 10-mm armor plate in front of the cockpit, and a 16-mm armor plate in the seat back and headrest. Devel­opment of the turbojet was delayed several times by technical prob­lems; as it turned out, the 1-3 was never powered by the VK-3 and was later converted into an 1-3U.

Specifications

Span, 8.978 m (29 ft 5.5 in); overall length, 14.83 m (48 ft 0.8 in); fuse­lage length (except cone), 12.275 m (40 ft 3.3 in); wheel track, 4.036 m (13 ft 2.9 in); wheel base, 5.04 m (16 ft 6.4 in); wing area, 30 m2 (322.9 sq ft); empty weight, 5,485 kg (12,090 lb); takeoff weight, 7,600 kg (16,750 lb); max takeoff weight, 8,954 kg (19,735 lb); fuel, 1,800 kg (3,970 lb); oil, 32 kg (70 lb); wing loading, 253.3-298.5 kg/m2 (51.9-61.2 Ib/sq ft); max operating limit load factor, 9.

Performance

Max speed, 1,274 km/h (688 kt) at sea level; 1,311 km/h at 5,000 m (708 kt at 16,400 ft); 1,775 km/h at 10,000 m (958 kt at 32,800 ft); climb to 5,000 m (16,400 ft) in 0.81 min; to 10,000 m (32,800 ft) in 1.9 min; service ceiling, 18,800 m (61,660 ft); landing speed, 190 km/h (103 kt); endurance, 1 h 46 min; range, 1,365 km (848 mi); takeoff roll, 390 m (1,280 ft); landing roll, 726 m (2,380 ft).