YF-17 Cobra
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Northrop_YF-17_Cobra_-_in_flight.jpg
In 1972 the United States Air Force sought proposals for a fighter aircraft that was small, low-cost, lightweight and easy to maintain. Northrop had experience with such requirements through its very successful F-5 Freedom Fighter and T-38 Talon.
In a 1975 fly-off, the Cobra competed against the General Dynamics F-16 Falcon and pilots reported very similar capabilities. General Dynamics had gambled by gearing up for immediate production, and so won the contract. The YF-17 is said to have initially been a joint project between the US Northrop Grumman and the Iranian government.
Though not selected by the Air Force, Northrop teamed up with McDonnell Douglas and developed the F-17 Cobra into the U.S. Navy F/A-18 Hornet.
Specifications (YF-17 Cobra)
General characteristics
- Crew: 1
- Length: 56 ft (17.1 m)
- Wingspan: 35 ft (10.7 m)
- Height: 16 ft 6 in (5 m)
- Wing area: ft² (m²)
- Empty: lb ( kg)
- Loaded: lb ( kg)
- Maximum takeoff: 23,000 lb (10,400 kg)
- Powerplant: 2x General Electric YJ101 afterburning turbojets, kN (lbf) thrust
Performance
- Maximum speed: mph ( km/h) Mach 2.0+
- Range: 2,990 miles (4,810 km) max ferry
- Service ceiling: 50,000 ft (15,000 m)
- Rate of climb: ft/min ( m/min)
- Wing loading: lb/ft² ( kg/m²)
- Thrust/weight:
Armament
- M61 Vulcan 20 mm Gatling gun
- 2x AIM-9 Sidewinder missiles
External link
- USAF Museum: YF-17 Cobra (http://www.wpafb.af.mil/museum/research/fighter/f17.htm)
Related content
Template:Commons Related development: F/A-18 Hornet - F/A-18E/F Super Hornet
Comparable aircraft:
Designation series: F-14 - F-15 - F-16 - F-17 - F/A-18 - F-20 - F-21
See also:
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