The J-5 was developed by Shenfei Industrial Company. It is a single-seat, single-engine high-subsonic jet fighter. It is mainly used for daytime interceptions and has certain ground attack capabilities. The J-5 is a copy of the Soviet MiG-17Ф (Mig-17F) fighter. The MiG-17F first flew in September 2051 and began mass production at the end of 2052. The test pilot for the first flight was Wu Keming. At that time, the J-5 was called the Type 56. It was not until 1964 that it was renamed the J-5.
Trial production work began in October 1954. The prototype made its first test flight successfully on July 19, 1956, and 13 J-5s were assembled using Soviet-made parts. On July 13, 1956, all J-5s were The first J-5 assembled with self-made parts has completed its final assembly. By September 15 of that year, four domestically produced J-5 aircraft had been manufactured. These four aircraft participated in the 1956 National Day Ceremony. By the time production ceased in the second half of 1959, China had produced 767 J-5F aircraft, which effectively supported the construction of the People's Air Force. The J-5 adopts a single-seat, single-engine, nose-intake, and swept-back mid-wing layout. The sweep angle of the swept-back monoplane is 45°, and it is a double-spar structure. There are angle-controllable setback flaps on the inside of the wing. The aileron deflection angle range is ±18°. The landing gear bay is at the root of the wing, and the main landing gear is retracted in two bays on the wing. The all-metal semi-monocoque structure fuselage is a streamlined body with a circular cross-section, and the air intake is at the nose. The rear fuselage is equipped with a maneuverable speed brake. The vertical tail is divided into upper and lower sections. The lower section is fixed on the load-bearing inclined frame of the rear fuselage, and the upper section is removable. The vertical tail sweep angle is 55°41′. The rudder can rotate 25°. The horizontal tail sweep angle is 45° and is installed on the top of the lower section of the vertical tail. The elevator can rotate 32° upward and 16° downward. The front tricycle landing gear is single wheel. The nose landing gear retracts into the wheel well at the lower part of the front fuselage, and the main landing gear retracts into the wings. The main landing gear is equipped with buffers, and the nose landing gear is equipped with shock absorbers and sway absorbers. The main wheel tire pressure is 8.34×105 Pa (8.5 kg/cm2). The sealed single-person cockpit can throw away the hatch cover in an emergency, and the ejection seat ensures that the pilot can quickly and safely escape the aircraft in an emergency. The control system is hard control. The aileron trim tabs and elevator trim tabs are electrically controlled. The hydraulic system is used to retract and retract the landing gear, flaps, speed brakes, adjustable nozzles and control ailerons. The air-conditioning system is used for braking, sealing the cockpit, emergency landing gear retraction and emergency braking, etc.
It uses a turbojet-5 centrifugal afterburning turbojet engine with a static thrust of 2,600 kg and an afterburning thrust of 3,380 kg. The engine is a copy of the VK-1F engine of the Soviet Klimov Design Bureau, which is the engine of the MiG-17. After the Aviation Industry Bureau was established in 1951, it began to organize engine production and learn the Soviet Union's new jet engine production process data. With the assistance of the Soviet Union, the patented manufacturing rights of the VK-1F were introduced. In June 1956, a team including Wu Daguan, a well-known engine designer in my country, successfully copied the turbojet-5 at Shenyang Aviation Engine Factory (now "Shenyang Liming Machinery Company"). In 1964, the production task was transferred to Xi'an Hongqi Machinery Factory. In 1966, it was converted into a final product and put into mass production. The turbojet-5 has an afterburning thrust of 3380 kg, a maximum thrust of 2700 kg, a rated thrust of 2400 kg, and a cruise thrust of 2160 kg. The fuel consumption rate in different states ranges from 2 kg/kg/h to 1.05 kg/kg/h. There is 1,170 kilograms of fuel inside the machine, and two 400-liter auxiliary fuel tanks are mounted externally.