Tupolev Tu-124

The Tupolev Tu-124 was developed as a response to the requirement of Aeroflot for a regional airliner that would take over the Ilyushin II-14 on domestic flights. Derived from the Tu-104 twin jet medium-range narrow-body airliner, the Tu-124 resembled a seventy-five percent of its predecessor with several improvements such as double-slotted flaps for better performance, as well as a large center-section airbrake and automatic spoilers that increased drag and reduced lift. It was introduced on October 2, 1962, and was built from 1960 until 1965. The aircraft was operated by Aeroflot, Iraqi Airways, and were also sold to a few military operators such as the Soviet Air Force and the Chinese Air Force.

The first production version Tu-124V can carry three crew members and fifty-six passengers on board. It has an external length of 30.58 meters, an external height of 4.36 meters, and a fuselage diameter of 2.9 meters. The wingspan is 25.55 meters and the wing area is 119.48 square meters. It has a tail height of 8.08 meters and a wheelbase of 10.7 meters. The empty weight is 22,900 kg, the maximum payload is 6000 kg, and the maximum takeoff weight is 37,500 kg. It has a fuel tank capacity of 3,500 US gal.

The aircraft is powered by a twin Soloviev D-20P engines rated at 11,900 lbf thrust each. It is a twin-spool low-bypass turbofan engine with a three-stage LP eight-stage HP axial flow compressor, cannular combustors with twelve flame tubes, a two-stage LP single-stage HP turbine, and a pressure spray oil system. The Tu-124 has a maximum speed of 520 knots and a cruise speed of 430 to 470 knots. It has a travel range of 1,100 nautical miles with maximum fuel and 3,000 kg of payload. The aircraft can fly up to 38,400 feet and can climb at a rate of 2,400 feet per minute.