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Northrop F-20 Tigershark



Initially known as the F-5G and officially redesignated F-20 in November 1982, the Tigershark single-seat tactical fighter was evolved as a company-funded development of the basic F-5E, having an 80% increase in engine thrust and only 21% increase in empty weight.

A much modified F-5E, the F-5G / F-20 has a General Electric F404-GE-100 low-bypass turbofan of 10,900 lb (4 943kg) dry thrust and 16,390 lb (7 433 kg) with afterburning, and an armament of two 20mm cannon and could carry up to 3175kg of ordnance on five stations. Three prototypes of the F-20, each embodying progressive improvements, were flown, these entering flight test on 30 August 1982, 26 August 1983 and 12 May 1984. A fourth prototype in the proposed fully-operational configuration was under construction when, following the October 1986 decision that an upgraded F-16A was to succeed F-4 and F-106 as the USAF's air defence fighter, Northrop terminated further development of the F-20 and ceased marketing efforts.

F-5G / F-20A Tigershark

General Electric F404-GE-100 turbofan, 10,900 lb (4 943kg) dry thrust / 16,390 lb (7433 kg) afterburning
Span: 7.70 m (25 ft 3 in)
Length: 14.38 m (47 ft 2 in)
Height: 4.22 m / 13 ft 10 in
Wing area: 186 sq ft (17,1 sq.m)
Empty weight: 11,220 lb (5 088 kg)
Loaded weight: 17,500 lb (7 936 kg)
Gross weight: 9379 kg (20 680 lb)
Wing loading: 94 lb/sq ft (464 kg/ sq.m)
Internal fuel: 4,440 lb (2 013 kg)
Maximum speed: 1489 km/h (925 mph)
Thrust/weight ratio: 0.94
Fuel fraction: 25.4 per cent
Range w/max.fuel: 2965 km / 1842 miles


Northrop F-20 Tigershark



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