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  • Antonov An-10

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    Description

    The Antonov An-10 (NATO reporting name: Cat) is a four-engined turboprop passenger transport aircraft designed in the Soviet Union.

    General Information

    A total of 104 aircraft were built, including the prototype and static test airframes, entering service with the Ukrainian Civil Aviation Directorate of Aeroflot from 27 April 1959, proving popular due to large cargo volume (when fitted with reduced seating) and excellent field performance, making the aircraft suitable for use on small undeveloped airfields. The Antonov Bureau simultaneously developed and produced the Antonov An-8 medium military transport, the An-10 civil airliner and military paratroop transport, as well as the Antonov An-12 military cargo transport.

     

    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 (in the two versions of the An-10A), 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 tailplane deicing system was retrofitted to all remaining aircraft.

     

    Variants
    Izdeliye U
    – The in-house designation of the four-engined passenger aircraft derived from the Izdeliye N An-8 project.[1]
    An-10 – The designation of the prototype and initial production versions fitted with Kuznetsov NK-4 or Ivchenko Ai-20A engines.
    An-10A – Production aircraft from December 1959 with increased seating, decreased empty weight/increased payload and Ivchenko AI-20K engines.
    An-10AS – several aircraft modified for small package cargo transport with no seats.
    An-10TS – (Transport/Sanitarny – transport/ambulance) 45 Aircraft ordered for the VTA (Voyenno-Transportnaya Aviatsiya – transport air arm), with 38 loaned to the Ministry of Civil Aviation.
    An-10KP – (Komandny Punkt – command post) A single aircraft (CCCP-11854) modified as an airborne command post for use at Sperenberg Airfield, near Berlin in the DDR.

     

     

    Antonov An-10 CCCP-11185.jpg

    Antonov An-10 overhead.jpg

    Antonov An-10 quarter view..jpg

    Antonov An-10A CCCP-11213.png

    Specifications

    Seats:
    Crew: 4 flight crew +cabin crew Capacity: 100 or 130 pax / 14,500 kg (32,000 lb)
    Length:
    34 m (111 ft 7 in)
    Wingspan:
    38 m (124 ft 8 in)
    Height:
    9.83 m (32 ft 3 in)
    Wing Area:
    120 sq m (1,300 sq ft)
    Wing Loading:
    430 kg/sq m (88 lb/sq ft)
    MTOW:
    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))
    Powerplant:
    4 × Ivchenko AI-20K turboprop engines, 3,000 kW (4,000 hp) each (equivalent)
    Vne:
    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)
    Stall Speed:
    Take-off speed: 190–210 km/h (120–130 mph; 100–110 kn)
    Range:
    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
    Landing Dist.:
    500–650 m (1,640–2,130 ft) with reverse pitch
    Service Ceiling:
    10,200 m (33,500 ft)

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