<H1>McDonnell Douglas F-4 Phantom II</h1>


F-4 Phantoms in formation.
The Phantom II was designed initially as a twinengined two-seat long-range all-weather fleet air defence fighter for the US Navy. Two prototypes were ordered on 18 October 1954, at which time the aircraft was designated AH-1. The designation was changed on 23 June 1955, with change of mission to missile fighter, and the prototype F4H-1 flew for the first time on 27 May 1958. The first production Phantom II was delivered to US Navy squadron VF-121 on 29 December 1960. Trials in a ground attack role led to USAF orders, and the basic USAF versions became the F-4B and F-4C respectively. An updating program covered the conversion of 116 F-4E aircraft to operational F-4G (Advanced Wild Weasel) configuration.

Other types


Power Plant

Two General Electric J79-GE-17A turbojet engines.


Accommodation

Crew of two in tandem under individual canopies. Optional dual controls.


Armament

Four Falcon, Sparrow, Sidewinder, Shrike or Walleye missiles, or two Bullpup missiles, on four mountings under fuselage and four underwing mountings. Various types of bombs including nuclear and cluster. Rocket pods, camera pods and gun pods are also possible. One mounted M61A-1 nose mounted gun.


Dimensions, external

Wing span: 11.77m (38ft, 7 1/2 inch)

Length overall: 19.20m (63ft)

Height overall: 5.02m (16ft, 5 1/2 inch)


Weigths

Weight empty: 13,757 kg (30,328 lb)

Max. TO weight: 28,030 kg (61,795 lb)


Performance

Max. level speed with external stores over Mach 2

Average speed: 504 knots (934 km/h, 580 mph)

Stalling speed: 150 knots (280 km/h, 174 mph)

Max. climb rate: 2847 m (9340 ft) /min

Ceiling: 16580 m (54500 ft)

Combat radius: +/- 618 nm (1145 km, 712 miles)


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