1. Supersonic Fighter Aircraft 2. The F-5 Tiger II, a single-seat twin-engined supersonic fighter aircraft, was developed by Northrop Grumman, US. The production of F-5A-21 began in 1970 by Northrop Grumman and at the same time the aircraft was renamed 'F-5E Tiger II. The avionics of the F-5E Tiger II are more sophisticated compared to the earlier version F-5A aircraft. It is the upgraded version of the F-5A Freedom fighter aircraft developed by Northrop Grumman in early 1959. 3. The aircraft is powered by two General Electric J85-GE-21B turbojet engines. Each engine can produce a thrust after burner of 22.2kN. It provides a maximum thrust-to-weight ratio compared to any other aircraft engine in the world. The delta shape of the aircraft was obtained by redesigning the forward wing root of its earlier version. The wings of the F-5E were equipped with enlarged leading edge extensions, thereby enhancing the wing area and maneuverability. 4. The advanced aircraft features a single-seat cockpit equipped with number of electronic systems, namely automatic flight control systems (AFCS), head-up display (HUD) and other auxiliary equipment. The aircraft comprises an air-to-air fire control radar system and a lead computing gun sight. The advanced radar system provides increased off-bore sight and doubles the range while enhancing the reliability. The avionics equipped in the aircraft include an inertial navigation system (INS), tactical air navigation (TACN) system, global positioning system (GPS), electronic counter measures (ECM), and hand on throttle and stick (HOTAS) system. 5. The F-5E Tiger II is armed with two 20mm point M39A2 cannons on either side of the nose. The M39A2 is a single-barrelled automatic cannon and can fire munitions at the rate of 1,500rpm. The aircraft features seven hard-points two under the wing tip, four under the two wings, and one under the fuselage pylon station. Four AIM-9 Sidewinder air-to-air missiles and two AGM-65 Mavericks air-to-surface missiles as well as rockets are mounted on the seven hard points. 6. General characteristics Length: 47 ft 4 in (14.45 m) Wingspan: 26 ft 8 in (8.13 m) Height: 13 ft 4 in (4.08 m) Wing area: 186 ft (17.28 m) Empty weight: 9,558 lb (4,349 kg) Loaded weight: 15,745 lb (7,157 kg) Max. takeoff weight: 24,722 lb (11,214 kg) Drag area: 3.4 ft (0.32 m) Performance Maximum speed: 917 kn (Mach 1.6, 1,060 mph, 1,700 km/h) ; at altitude Range: 760 nmi (870 mi, 1,405 km) Ferry range: 2,010 nmi (2,310 mi, 3,700 km[147]) Service ceiling: 51,800 ft (15,800 m) Rate of climb: 34,400 ft/min (175 m/s) 7. http://en.wikipedia.org/wiki/Northrop_F-5 http://www.airforce-technology.com/projects/f- 5tiger2/ http://www.fas.org/man/dod-101/sys/ac/f-5.htm