Mig 13 / I-250

Specifications

1st Flight 1945

Crew: 1

Height: 3.7 m (12 ft 2 in)

Wing area: 14.99 m2 (161.4 sq ft)

Empty weight: 2,797 kg (6,166 lb)

Gross weight: 3,650 kg (8,047 lb)

Fuel capacity: 612 litres (135 imp gal; 162 US gal) / 570 kg (1,256.6 lb) fuel and oil

Powerplant: 1 × Klimov VK-107R V-12 liquid-cooled piston engine, 1,230 kW (1,650 hp) with VRDK – equivalent power 2,088 kW (2,800 hp)

Powerplant: 1 × Khalshchevnikov Uskoritel VRDK motorjet, 2.9 kN (660 lbf) thrust (VRDK – Vozdushno-Reaktivnyi Dvigatyel Kompressornyi)

Propellers: 3-bladed AV-10P-60, 3.1 m (10 ft 2 in) diameter constant-speed propeller

Performance

Maximum speed: 820 km/h (510 mph, 440 kn)

Range: 790 km (490 mi, 430 nmi)

Service ceiling: 11,900 m (39,000 ft)

Wing loading: 245 kg/m2 (50 lb/sq ft)

Armament

3 × 20 mm (0.787 in) Berezin B-20 auto cannon (160 rounds each)

Variants

The Mikoyan-Gurevich I-250 (Samolet N), aka MiG-13, was a Soviet fighter aircraft developed as part of a crash program in 1944 to develop a high-performance fighter to counter German turbojet-powered aircraft such as the Messerschmitt Me 262.

The Mikoyan-Gurevich design bureau decided to focus on a design that used something more mature than the jet engine, which was still at an experimental stage in the Soviet Union, and chose a mixed-power solution with the VRDK (Vozdushno-Reaktivny Dvigatel Kompressornyi – air reaction compressor jet) motorjet powered by the Klimov VK-107 V12 engine.

While quite successful when it worked, with a maximum speed of 820 km/h (510 mph) being reached during trials, production problems with the VRDK fatally delayed the program and it was cancelled in 1948 as obsolete.

12 aircraft were produced

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