Tupolev Tu-104

Narrow-body jet airliner introduced in 1956

Overview

Tupolev Russia ICAO: T104 1956–1960

The Tupolev Tu-104 was a Soviet airliner produced by Tupolev from 1956 to 1960. It was a medium-range twin-engine turbojet-powered aircraft and the sole jet airliner that operated from 1956 until 1958 in the world. The aircraft was developed from the Tupolev Tu-16 and was introduced on September 15, 1956, with Aeroflot. It was retired in 1981 and had a total number of 201 aircraft built.

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Specifications

Units
Engine
2 × Mikulin AM-3M-500
Engine type
Jet
Thrust
2 × 21,400 lbf · 95 kN
Avionics
—
Wing tips
No winglets
Seats
115
Crew
—
Cabin width
—
Cabin height
—
Cabin length
—
Exterior length
131 ft 5 in  ·  40.06 m
Tail height
39 ft 1 in  ·  11.90 m
Fuselage diameter
11 ft 2 in  ·  3.40 m
Wing span
113 ft 4 in  ·  34.54 m
Baggage volume
—
Gross weight
—
Empty weight
—
Max takeoff weight
172,000 lb  ·  78,000 kg
Max landing weight
—
Max payload
26,500 lb  ·  12,000 kg
Fuel capacity
7,000 gal · 26,500 L · 21,200 kg (Jet A)
Max cruise speed
510 kt  ·  587 mph  ·  945 km/h
Maximum speed
—
Cruise speed
—
Approach speed
145 kt  ·  167 mph  ·  269 km/h
Range
1,480 nm  ·  1,700 mi  ·  2,740 km
Fuel burn
—
Ceiling
39,000 ft  ·  11,900 m
Rate of climb
2,000 ft/min  ·  10 m/s
Takeoff distance
7,200 ft  ·  2,200 m
Landing distance
6,050 ft  ·  1,850 m
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Aeroflot Tupolev Tu-104B

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Operational Context

The Tupolev Tu-104 was developed as a response to the need of Aeroflot for a modern airliner with improved capacity and better performance compared to the piston-engined aircraft that were existing then. The new Tu-104 was derived from the Tu-16 Badger twin-engine jet bomber with few improvements. The Tu-104 had several variants produced.

The Tupolev Tu-104B version had various modifications and has a lengthened fuselage of 40.06 meters, with an external height of 6 meters and a fuselage diameter of 3.4 meters. The aircraft can accommodate seven crew members and fifty to one hundred and fifteen passengers on board. It has a wingspan of 34.54 meters and a wing area of 183 square meters minus the leading-edge extension. The tail height is 11.9 meters and the wheelbase is 15.1 meters. On April 15, 1959, the aircraft started its revenue service with Aeroflot flying from Moscow to Saint Petersburg.

The aircraft has an empty weight of 43,800 kg, a gross weight of 78,100 kg, and a maximum payload of 12,000 kg. The normal fuel capacity is 21,000 kg while the maximum is 26,500 kg. The Tu-104B is powered by two Mikulin AM-3M-500 engines. It is a turbojet engine with an axial-flow single-stage LP eight-stage HP compressor, fourteen can combustion chambers, and an axial-flow two-stage turbine. Each engine produces a maximum thrust of 21,400 lbf.

The aircraft has a maximum speed of 510 knots. It has a cruise speed of 400 to 460 knots at 32,808 to 39,370 feet. The range is 1,140 nautical miles with 12,000 kg of payload and 5,650 kg of fuel reserve and 1,485 nautical miles with 8,150 kg of payload and 5,650 kg of fuel reserve. The Tu-104 can fly up to 39,000 feet and can climb at a rate of 2,000 feet per minute. The takeoff run at maximum takeoff weight is 2,200 meters and the landing run at normal landing weight is between 1,450 meters to 1,850 meters without brake parachute.