Aviatik Alliance Aleks-251
|Role||Six seat amphibious aircraft|
|Designer||Aleksey Tantsyrev and Sergey Popov|
|First flight||10 September 2010|
Design and development
The Alleks-251 has had a long development time. The project was first made public in 2003 by the Rida design bureau, who intended to make the first flight in late 2004. There were no further progress reports until the foundation of the Aviatik Alliance Company and the appearance of the near-complete prototype at the Moscow Salon in August 2009. The aircraft flew for the first time on 10 September 2010.
The Aleks-251 is mostly constructed of metal, only using composites in the nosecone, engine cowlings and fin tip. It has a parallel chord, square tipped wing with a full-span combination of slotted ailerons and flaps. The parasol configuration allows the twin 127 kW (170 hp) LOM 332S inverted inline engines to be mounted forward of and under the wing, close together. The wing is braced to the fuselage with a pair of inverted V-struts to the engine mountings.
The hull of the Aleks-251 has a single step and is divided into six watertight compartments. The cabin, 3.10 m (10 ft 2 in) long, 1.40 m (4 ft 7 in) wide and 1.30 m (4 ft 3 in) high seats the pilot and six passengers in three rows, the central one with three seat, the front pair just ahead of the wing leading edge but behind the propeller disks. Other seating configurations, e.g. for medical evacuation with a stretcher and two attendants, are possible. Access is by hinged transparencies. A straight edged, swept back fin carries both the horn-balanced rudder and, at about ⅓ height, the parallel chord, strongly dihedralled tailplane. The port elevator and, in production aircraft the rudder, have trim tabs.
On water the Aleks-251 is stabilized by a pair of floats, each mounted on a single strut which rotates their float to the wing tip once airborne. On land it has a fully retractable tailwheel undercarriage. The cantilever main legs rotate forwards by much more than 90° to retract the wheels into the upper nose forward of the cabin windscreen. A MVEN ballistic recovery parachute is fitted.
Data from Jane's All the World's Aircraft 2011/12
- Crew: 1
- Capacity: up to 6 passengers
- Length: 10.54 m (34 ft 7 in)
- Wingspan: 13.20 m (43 ft 4 in)
- Height: 3.66 m (12 ft 0 in) on land
- Wing area: 19.80 m2 (213.1 sq ft) gross
- Empty weight: 1,610 kg (3,549 lb)
- Max takeoff weight: 2,500 kg (5,512 lb) production aircraft; prototype 2,100 kg (4,630 lb)
- Fuel capacity: 700 L (185 US gal, 154 Imp gal)
- Powerplant: 2 × LOM M332S four cylinder piston, 127 kW (170 hp) each in prototype
- Propellers: 2-bladed, 1.855 m (6 ft 1.0 in) diameter
- Maximum speed: 240 km/h (149 mph; 130 kn) estimated for production aircraft maximum take-off weight, are the other performance figures
- Cruising speed: 200 km/h (124 mph; 108 kn)
- Stall speed: 95 km/h (59 mph; 51 kn)
- Range: 740 km (460 mi; 400 nmi) with 30 min reserves, 4 passengers
- Ferry range: 2,200 km (1,367 mi; 1,188 nmi)
- Rate of climb: 4.0 m/s (790 ft/min) maximum, at sea level
- Wing loading: 126.3 kg/m2 (25.9 lb/sq ft)
- Two-screen EFIS, Garmin GNS 430 GPS, Bendix/King KR 87 ADF, L-3 WX 500 Stormscope and Garmin communications systems.