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Antonov An-10 Ukraina

Development of a four-engine airliner intended for use on routes from 500 to 2000 kilometres (310 to 1,262 miles) began at the end of 1955.

Inspired by the Izdeliye N passenger version of the Antonov An-8, the Antonov design bureau developed the Izdeliye U , a four-engined aircraft with a similar layout to the An-8, but with increased dimensions and a circular-section pressurised fuselage.

Early in the design process the choice of engines was between the Kuznetsov NK-4 and the Ivchenko AI-20, and despite superior performance the Kuznetsov NK-4 was eliminated and the Ivchenko AI-20 selected, partly due to the Central Committee of the Communist Party of Ukraine which wanted as much as possible produced in Ukraine, where the Ivchenko factory was.

The first prototype flew on 7 March 1957, revealing poor directional stability which led to a taller vertical fin, and later to hexagonal auxiliary fins at the tips of the tailplane.

Entering production at Zavod factory No.64, Voronezh in 1957, the initial three aircraft were delivered with Kuznetsov NK-4 engines, due to non-availability of the Ivchenko AI-20 engines.

From 1958, production aircraft were delivered with the Ivchenko AI-20A engines which boasted a longer service life and comparable performance compared to the Kuznetsov engines.

The new aircraft was displayed to the public for the first time in July 1957, the design was approved for mass production after testing was completed in June 1959.

Aeroflot began operations with the An-10 from 22 July 1959 on the Moscow – Simferopol route.

Configured with 85 seats, the cabin was spacious and well-appointed with comfortable seats widely spaced, giving plenty of legroom, but due to the low cabin floor and wide diameter, there was much unusable space which limited baggage and cargo volume.

The inefficient use of cabin volume contributed greatly to the low payload/TOW ratio which was much lower than that of the contemporary Ilyushin Il-18, but which was still higher than the Tupolev Tu-104.

A later production version, the An-10A, addressed some of the efficiency concerns by increasing the number of seats from 85 to 89 and 100, then to 117–118 and finally 132 through reducing seat pitch and changing the cabin layout.

Powered by Ivchenko AI-20K engines the An-10A demonstrated superior performance and an increased maximum payload of 14.5 Tonnes (31,970 lb).

The auxiliary endplate fins eventually gave way to improved splayed ventral fins under the rear fuselage.

The directional stability was now acceptable and the new ventral fins also improved longitudinal stability at high G and on landing approach, as well as delaying the onset of Mach buffet to M0.702.

Due to being sited in an area of flow separation, the new ventral fins also caused unpleasant vibrations.

Following results of flight tests and at least two fatal crashes, an effective tail plane de-icing system was retro fitted to all remaining aircraft.




100 or 130 pax / 14,500 kg (32,000 lb)


34 m (111 ft 7 in)


38 m (124 ft 8 in)


9.83 m (32 ft 3 in)

Wing area

120 m2 (1,300 sq ft)


222 m3 (7,800 cu ft) cabin volume

Under floor hold volume

32 m3 (1,100 cu ft)

Max take-off weight

55,100 kg (121,475 lb)

Fuel capacity

13,000 l (3,400 US gal; 2,900 imp gal) (10,250 kg (22,600 lb))


4 × Ivchenko AI-20K turboprop engines,

3,000 kW (4,000 hp) each (equivalent)


4-bladed AV-68 reversible-pitch constant-speed propellers,

4.5 m (14 ft 9 in) diameter


Maximum speed

715 km/h (444 mph, 386 kn)

Cruise speed

680 km/h (420 mph, 370 kn) maximum at 10,000 m (33,000 ft)

Economical cruise speed

630 km/h (390 mph; 340 kn) at 10,000 m (33,000 ft)

Take-off speed

190–210 km/h (120–130 mph; 100–110 kn)


1,200 km (750 mi, 650 nmi) with max payload + 60 minutes reserve fuel

4,075 km (2,532 mi) with max fuel 8,440 kg (18,610 lb) payload and no reserves

Service ceiling

10,200 m (33,500 ft)

Wing loading

430 kg/m2 (88 lb/sq ft)


4.4 kg/kW (7.2 lb/hp)

Landing run

500–650 m (1,640–2,130 ft) with reverse pitch.


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