|Jurgis Kairys in his Su-31|
|Developed from||Sukhoi Su-29|
Design and development
The design of the aircraft started in 1991 as a single-seat development of the earlier Sukhoi Su-29 with a more powerful Vedeneyev M-14PF engine and new landing gear. The low-wing cantilever monoplane first flew in June 1992 as the Su-29T and the first production aircraft flying in 1994.
- Prototype single-seat aerobatic monoplane
- Production variant with fixed landing gear, sometimes known as the Su-31T.
- Improved variant with a pilot extraction system.
- Further improved variant of the Su-31M with weight reduction, single piece canopy/windscreen and larger wing introduced in 1999.
- Proposed retractable landing gear variant of the Su-31T.
- Export variant of the Su-31T
- Modified experiment for wider aerobatic envelope.
Data from Su-26, 29, 31 Specifications
- Crew: 1
- Length: 6.83 m (22.41 ft)
- Wingspan: 7.80 m (25.59 ft)
- Height: 2.76 m (9.06 ft)
- Wing area: 11.83 m² (127.34 sq ft)
- Empty weight: 700 kg (1,543 lb)
- Max. takeoff weight: 1,050 kg (2,315 lb)
- Powerplant: 1 × Vedeneyev M-14PF, 294 kW (400 hp)
- Never exceed speed: 450 km/h (243 knots, 280 mph)
- Maximum speed: 331 km/h (178 knots, 205 mph)
- Stall speed: 106 km/h (57 knots, 66 mph)
- Range: 1,100 km (594 nmi, 684 mi)
- Rate of climb: 24 m/s (4,724 ft/min)
- Load factor: -10g to 12g
- Roll rate: 7 rad/sec (401 deg/sec)
- Related development
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