McDonnell Douglas F4-G Phantom

Role: Twin-engined two-seat all-weather fighter aircraft.

DESIGN FEATURES: Cantilever low-wing monoplane. Wing section NACA 0006.4-64 (mod) at root, NACA 0004-64 (mod) at wing fold line, NACA 0003-64 (mod) at tip. Average thickness/chord ratio 5.1 per cent. Incidence 1 degrees. Dihedral, inner panels 0 degrees, outer panels 12 degrees. Sweepback 45 degrees on leading-edges. Outer panels have extended chord and dihedral of 12 degrees.

STRUCTURE: Centre-section and centre wings form one-piece structure from wing fold to wing fold. Portion that passes through fuselage comprises a torsion-box between the front and main spars (at 15 per cent and 40 per cent chord) and is sealed to form two integral fuel tanks. Spars are machined from large forgings. Centre wings also have forged rear spar. Centreline rib, wing-fold ribs, two intermediate ribs forward of main spar and two aft of main spar are also made from forgings. Wing skins machined from aluminium panels 0.0635 m (2 1/2 in) thick, with integral stiffening. The fuselage is an all-metal semi-monocoque structure built in forward fuselage fabricated in port and starboard halves, so that most internal wiring and finishing can be done before assembly. Keel and rear sections make use of steel and titanium.

LANDING GEAR: Hydraulically retractable tricycle type, mainwheels retracting inward into wings, nose unit rearward. Single wheel on each main unit, with tyres size 30 x 11.5 Type VIII; twin-wheels on nose unit, which is steerable and self-centring and can be lengthened pneumatically to increase the aircraft's angle of attack for take-off. Brake-chute housed in fuselage tailcone. Mk II anti-skid system.

POWER PLANT: Two General Electric J79-GE-17A turbojet engines (each rated 79.6 kN; 17,900 lb st with afterburning). Variable-area inlet ducts monitored by air data computer. Integral fuel tankage in wings, between front and main spars, and in seven fuselage tanks, with total capacity of 7022 litres (1855 US gallons; 1545 Imp gallons). Provision for one 2270 litre (600 US gallon; 500 Imp gallon) external tank under fuselage and two 1400 litre (370 US gallon; 308 Imp gallon) underwing tanks. Equipment for probe-and-drogue and 'buddy tank' flight refuelling, with retractable probe in starboard side of fuselage. Oil capacity 39 litres (10.3 US gallons; 8.6 Imp gallons).

ACCOMMODATION: Crew of two in tandem on Martin-Baker Mk H7 ejection seats, under individual rearward hinged canopies. Optional dual controls.

ARMAMENT: Four Falcon, Sparrow, Sidewinder, Shrike or Walleye missiles, or two Bullpup missiles, on four semi-submerged mountings under fuselage and four underwing mountings. Provision for carrying alternative loads of up to 7250 kg (16000 lb) of nuclear or conventional bombs and stores on seven attachments under wings and fuselage. Stores which can be carried include B-28, -43, -57, -61 nuclear bombs; M117, M118, M129, MC-1, Mk 36, Mk 81, Mk 82, Mk 83 and Mk 84 bombs; MLU-10 land mine; BLU-1, -27, -52 and -76 fire bombs; cluster bombs; practice bombs; flares; rocket packs; ECM pods; gun pods; spray tanks; tow targets' Pave Knife pod; and AAVSIV camera pod. One M61A-1 nose-mounted gun.

Aircraft Measures:
Length:63 ft.
Height: 16 ft., 3 in.
Wingspan: 38 ft., 5 in.
Loaded Weight: 60,630

Aircraft Performance:
Maximum Speed: 1,464 mph
Service Ceiling: 59,200 ft.
Range: 2,300 miles
Thrust: 35,800 lbs.

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