North American FJ-4 Fury

Carrier fighter retired in the late 1960s

North American FJ-4B Fury © D. Miller

Overview

North American Aviation (NAA) United States ICAO: FJ4 1954–1968

The North American FJ-4 Fury was manufactured by the North American Aviation as a carrier-capable fighter aircraft intended for the United States Navy and United States Marine Corps. It was developed from the FJ-2/-3 Fury and first flew in October 1954. The aircraft was retired in the late 1960s with a total number of 374 FJ-4s built.

Live Fleet Activity (FJ4)

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Specifications

Units
Engine
1 × Wright J65-W-16A
Engine type
Jet
Thrust
7,700 lbf · 34 kN
Avionics
—
Wing tips
No winglets
Seats
1
Crew
—
Cabin width
—
Cabin height
—
Cabin length
—
Exterior length
36 ft 5 in  ·  11.10 m
Tail height
13 ft 9 in  ·  4.20 m
Fuselage diameter
4 ft 7 in  ·  1.40 m
Wing span
39 ft 1 in  ·  11.90 m
Baggage volume
—
Gross weight
—
Empty weight
—
Max takeoff weight
23,700 lb  ·  10,800 kg
Max landing weight
—
Max payload
4,850 lb  ·  2,200 kg
Fuel capacity
840 gal · 3,200 L · 2,500 kg (Jet A)
Max cruise speed
590 kt  ·  679 mph  ·  1,093 km/h
Maximum speed
—
Cruise speed
—
Approach speed
—
Range
1,755 nm  ·  2,020 mi  ·  3,250 km
Fuel burn
—
Ceiling
46,800 ft  ·  14,300 m
Rate of climb
7,660 ft/min  ·  39 m/s
Takeoff distance
—
Landing distance
—
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North American FJ-4 Fury

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Operational Context

On October 28, 1954, the FJ-4 took its first flight. In comparison with the earlier FJ-3, the FJ-4 Fury was fitted with thinner swept wings with a 6 percent thickness to chord ratio. It has a wingspan of 11.9 meters and an increased wing area of 31.46 square meters.

It was also fitted with skin panels from solid alloy plates. Slight camber at the back if the leading edge enhanced low-speed capabilities of the aircraft. The main landing gear was significantly changed to collapse wheel and strut in the outline of the wing. It has a wheelbase of 5.12 meters.

The main wheel track was increased and since they were nearer the center of gravity, a lesser weight on the nosewheel was produced.

The single-seat FJ-4 has an exterior length of 11.1 meters, an exterior height of 3.2 meters, a tail height of 4.2 meters, and a fuselage diameter of 1.4 meters. It has an empty weight of 6,000 kg, a loaded weight of 6,000 kg, and a maximum takeoff weight of 10,750 kg. The maximum payload is 2,200 kg and the fuel tank capacity is 840 US gal. It has fifty percent more fuel compared to the FJ-3.

The FJ-4 is powered by a single Wright J65-W-16A engine. It is an axial-flow turbojet with a thirteen-stage axial compressor, annular combustors, and two-stage axial turbine. The engine is rated at 7,700 lbf thrust. The aircraft has a maximum speed of 590 knots at sea level. The travel range is 1,755 nautical miles with 2 x 200 gal drop tanks and two AIM-9 missiles. It can fly up to 46,800 feet and can climb at a rate of 7,660 feet per minute.

The aircraft can be loaded with four 20 mm Colt Mk 12 cannons, six LAU-3/A 70 mm rocket pods, four AIM-9 Sidewinder short-range air-to-air missiles, or few more configurations of rocket pods, and 1,400 kg of underwing ordnance including missiles.