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Tupolev Tu-244

By Wikipedia,
the free encyclopedia,

http://en.wikipedia.org/wiki/Tupolev_Tu-244

Tu-244
Future Rendering Of The Tupolev Tu-244
Role Supersonic transport
Manufacturer Tupolev
Designed by Tupolev
First flight 2015?
Status In development, may be canceled due to lack of funds.
Primary users None
None
Produced Production For 2011?
Number built 0
Unit cost Not Developed
Developed from Tupolev Tu-144

The Tupolev Tu-244 is a proposed supersonic transport (SST) aeroplane developed from the Tu-144 design produced in 1967. Tupolev estimate it will be available between 2010-2015. It implements novel features such as Cryogenic fuel to enable flight distance of up to 10,000 km (6,214 mi), and may carry up to 300 passengers. If built it will be Russia's second supersonic commercial use passenger jet.

History

The draft work began 1979, and when the project ended in 1993 substantial progress had already been made during the interpretation. In particular the air resistance within the range around Mach 2 was only 50% higher than with a conventional passenger airline with Mach 0.9.

The nearly circular trunk (3.9 m width, 4.1 m height) and the wing unit should consist to a large extent of titanium composite materials. The engines will be higher performance modifications of the Samara NK-321-Turbofan, used also with the Tu-160. Adjustable air intakes from the Tu-160 may be included. Projected passenger capacity is 311.

Fly-by-wire is intended for flight control. Rather than use a tilting nose, video cameras should provide the crew the necessary views for landings.

Specifications (proposed)

General characteristics

  • Capacity: 250/320 passengers
  • Length: 88.7 m (291 ft)
  • Wingspan: 54.77 m (179 ft)
  • Height: Unknown (Unknown)
  • Wing area: 1,200 m² (12,916 ft²)
  • Empty weight: 172,000 kg (379,000 lb)
  • Max takeoff weight: 350,000 kg (771,600 lb)
  • Powerplant:Kuznetsov NK-321 turbofans, 33,000 kg () each
  • Height from ground (to the top of the tail fin): 16.9 m (55 ft)
  • Height from lowest point (engine): 12.45 m (41 ft)
  • Fuselage external width: 3.9 m (12 ft)
  • Fuselage external height: 4.1 m (13 ft)
  • Wing length (Root Chord): 54.7 m (179 ft)
  • Main gear track: 8 m (26 ft)
  • Max weight of fuel: 178,000 kg (392,425 lb)

Performance


See also

Related development

Comparable aircraft

External links




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Published - July 2009














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