McDonnell Douglas F-4 Phantom II

The McDonnell Douglas F-4 Phantom II is an American tandem-seat, twin-engined, all-weather, long-range supersonic interceptor fighter-bomber. Later adapted for the reconnaissance and Wild Weasel (Suppression of Enemy Air Defenses) missions. The maiden flight took place on May 27, 1958, entering service on December 30, 1960. Designed for the US Navy, it also served with the USAF, USMC, and other countries. The US military began to replace the F-4 during the 1980s, reconnaissance, and Wild Weasel variants in 1996. Production ended in 1981, with over 5,000 airframes built.

The airframe is constructed mainly of steel, titanium and aluminium with a semi-monocoque fuselage. Low mounted sweptback cantilever wings; the inner panels have 0° dihedral, outer panels 12°— cantilever tail unit with a 23º anhedral all-moving tailplane and retractable tricycle undercarriage.

Powered by two General Electric J79 afterburning turbojet engines, the F-4J has a maximum speed of 255o km/h (1584 mph), a 21,336 m (70,000 ft) service ceiling and maximum range of 3148 km (1956 mi).

The Phantom was without guns until the introduction of the F-4C with a 20 mm (.79 in) M61A1 Vulcan Gatling cannon external gun pod. The -E variant was the first to have an internally mounted cannon. With nine external hard-points, the Phantom II can carry up to 7,250 kg (16,000 lb) of payload, four semi-recessed under the fuselage, two under each wing and one under-fuselage on centre-line. Ordnance included missiles, guided and unguided bombs, rockets, mission-specific pods and drop tanks.