McDonnell Douglas F-4 Phantom II
Flat Wing Aspect Ratio
2.77
Entry Into service
1960-12-30
Maximum Take-Off Weight
28.0297 t (paragliders: kg)
Total Fuel Capacity
7548.111
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All data (26 fields)
- Name
- McDonnell Douglas F-4 Phantom II
- Manufacturer
- McDonnell Aircraft
- Description
- The McDonnell Douglas F-4 Phantom II is an American tandem two-seat, twin-engined, all-weather, long-range supersonic jet interceptor and fighter-bomber that was developed by McDonnell Aircraft for the United States Navy.
- First Flight
- 1958-05-27
- Entry Into service
- 1960-12-30
- Production End
- 1981-01-01
- Designer
- McDonnell Aircraft
- Length (m)
- 19.2
- Height (m)
- 5
- Cockpit Crew
- 2
- Max Speed (km/h)
- 2370
- Cruise Speed (km/h)
- 940
- Max Ceiling (m)
- 18288
- Rate of Climb (m/s)
- 209.804
- Armament
- E-model has a 20 mm (0.787 in) M61A1 Vulcan cannon mounted internally under the nose, 640 rounds; Up to 18,650 lb (8,480 kg) of weapons on nine external hardpoints, including general-purpose bombs, cluster bombs, TV- and laser-guided bombs, rocket pods, air-to-ground missiles, anti-ship missiles, gun pods, and nuclear weapons. Reconnaissance, targeting, electronic countermeasures, baggage pods, a…
- Max Mach (Mach)
- 2.23
- National Origin
- United States of America
- Number Built
- 5195
- Powerplant Description
- 2 × General Electric J79-GE-17A after-burning turbojet engines
- Primary Users
- United States Air Force (historical)
- Status
- In limited service
- Wikipedia Article (URL)
- en.wikipedia.org/wiki/McDonnell_Douglas_F-4_Phantom_II
- Flat Wing Span (m)
- 11.7
- Flat Wing Area (m²)
- 49.2
- Flat Wing Aspect Ratio
- 2.77
- Number of Engines
- 2