The Northrop F5 is a family of supersonic light fighter aircraft initially designed as a privately funded project in the late 1950s by Northrop Corporation. There are two main models, the original F5A and F5B Freedom Fighter variants and the extensively updated F5E and F5F Tiger II variants. The design team wrapped a small, highly aerodynamic fighter around two compact and highthrust General Electric J85 engines, focusing on performance and a low cost of maintenance. Smaller and simpler than contemporaries such as the McDonnell Douglas F4 Phantom II, the F5 cost less to procure and operate, making it a popular export aircraft. Though primarily designed for a day air superiority role, the aircraft is also a capable groundattack platform. The F5A entered service in the early 1960s. During the Cold War, over 800 were produced through 1972 for U.S. allies. Though at the time the United States Air Force (USAF) did not have a need for a light fighter, it did procure approximately 1,200 Northrop T38 Talon trainer aircraft, which was based on Northrop's N156 fighter design.
After winning the International Fighter Aircraft Competition, a program aimed at providing effective lowcost fighters to American allies, in 1970 Northrop introduced the secondgeneration F5E Tiger II in 1972. This upgrade included more powerful engines, larger fuel capacity, greater wing area and improved leading edge extensions for better turn rates, optional airtoair refueling, and improved avionics including airtoair radar. Primarily used by American allies, it remains in US service to support training exercises. It has served in a wide array of roles, being able to perform both air and ground attack duties; the type was used extensively in the Vietnam War.
The F5 was also developed into a dedicated reconnaissance aircraft, the RF5 Tigereye. The F5 also served as a starting point for a series of design studies which resulted in the Northrop YF17 and the F/A18 naval fighter aircraft.
The design effort was led by Northrop vice president of engineering and aircraft designer Edgar Schmued who previously at North American Aviation had been the chief designer of the successful North American P51 Mustang and F86 Sabre fighters. Schmued recruited a strong engineering team to Northrop.
From this tour, Schmued gave his team the goal of reversing the trend in fighter development towards greater size and weight in order to deliver an aircraft with high performance, enhanced maneuverability, and high reliability, while still delivering a cost advantage over contemporary fighters.Recognizing that expensive jet aircraft could not viably be replaced every few years, he also demanded "engineered growth potential" allowing service longevity in excess of 10 years.

General characteristics

Crew: 1
Length: 48 ft 2.25 in (14.6876 m)
Wingspan: 26 ft 8 in (8.13 m)
27 ft 11.875 in (8.53123 m) with wingtip missiles
Height: 13 ft 4.5 in (4.077 m)
Wing area: 186 sq ft (17.3 m2)
Aspect ratio: 3.86
Airfoil: NACA 65A004.8
Empty weight: 9,583 lb (4,347 kg)
Gross weight: 15,745 lb (7,142 kg) clean
Max takeoff weight: 24,675 lb (11,192 kg)
Fuel capacity:
Internal fuel: 677 US gal (564 imp gal; 2,560 l)
External fuel: up to 3x 275 US gal (229 imp gal; 1,040 l) droptanks
Lifttodrag ratio: 10.0
Zerolift drag coefficient: CD0.0200
Frontal area: 3.4 sq ft (0.32 m2)
Powerplant: 2 × General Electric J85GE21 afterburning turbojet engines, 3,500 lbf (16 kN) thrust each dry, 5,000 lbf (22 kN) with afterburner
Performance

Maximum speed: Mach 1.63 (1,741 km/h; 1,082 mph) at 36,000 ft (11,000 m)
Maximum cruise speed: Mach 0.98 (1,050 km/h; 650 mph) at 36,000 ft (11,000 m)
Economical cruise speed: Mach 0.8 (850 km/h; 530 mph) at 36,000 ft (11,000 m)
Stall speed: 124 kn (143 mph, 230 km/h) 50% internal fuel, flaps and wheels extended
Never exceed speed: 710 kn (820 mph, 1,310 km/h) IAS
Range: 481 nmi (554 mi, 891 km) clean
Combat radius (20 min reserve): 120 nmi (140 mi; 220 km) with 2x Sidewinders + 5,200 lb (2,400 kg) ordnance, with 5 minutes combat at max power at sea level
Ferry range: 2,010 nmi (2,310 mi, 3,720 km)
Ferry range (20 min reserve): 1,385 nmi (1,594 mi; 2,565 km) drop tanks retained
Ferry range (20 min reserve): 1,590 nmi (1,830 mi; 2,940 km) drop tanks jettisoned
Service ceiling: 51,800 ft (15,800 m)
Service ceiling one engine out: 41,000 ft (12,000 m)
Rate of climb: 34,500 ft/min (175 m/s)
Lifttodrag: 10:1
Wing loading: 133 lb/sq ft (650 kg/m2) maximum
Thrust/weight: 0.4 takeoff thrust at maximum takeoff weight
Takeoff run: 2,000 ft (610 m) with two Sidewinders at 15,745 lb (7,142 kg)
Takeoff run to 50 ft (15 m): 2,900 ft (884 m) with two Sidewinders at 15,745 lb (7,142 kg)
Landing run from 50 ft (15 m): 3,701 ft (1,128 m) without brakechute
Landing run from 50 ft (15 m): 2,500 ft (762 m) with brakechute

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