BOEING (MCDONNELL DOUGLAS) F-4 'Phantom II'

The Phantom II was developed initially as a twin-engined two-seat long-range all-weather attack fighter for service with the US Navy.
A letter of intent to order two prototypes was issued on October 18, 1954, at which time the aircraft was designated AH-1.
The designation was changed to F4H-1 on May 26, 1955, with change of mission to missile fighter, and the prototype XF4H-1 flew for the first time on May 27, 1958.
The first production Phantom II was delivered to US Navy Squadron VF-101 in December 1960.
Trials in a ground attack role led to USAF orders, and the basic USN and USAF versions became the F-4B and F-4C.

Folding wings and arrester gear retained.
Sufficient F-4Cs were modified to equip two squadrons for a defence suppression role under the USAF's Wild Weasel programme.
These aircraft carry ECM warning sensors, jamming pods, chaff dispensers and anti-radiation missiles.
First F-4C flew on May 27, 1963.

Multirole fighter for air superiority, close support and interdiction missions with USAF.
Has internally mounted M-61A1 multibarrel gun, improved (AN/APQ-120) fire-control system and J79-GE-17 turbojet engines (each 79.6 kN; 17,900 lb st).
Avionics updated in later aircrafts, including the ASX-1 TISEO (Target Identification System, Electro-Optical), and a modified ASG-26 computing sight.
Enhanced range of weapons became compatible, including guided bombs family (Mk 84/118 LGB/IR/EO) as well as ALQ-71, -72, -87, and -101 ECM pods.
An additional seventh fuselage fuel cell added to compensate for centre of gravity movement.
Martin-Baker zero-zero ejector seats were fitted in 1972 (never reached operational status for Vietnam), and slats were added to the outer wing section.
First production F-4E delivered to USAF on October 3, 1967.
Supplied to the Israeli Air Force, Hellenic Air Force, Turkish Air Force, Republic of Korea Air Force and Islamic Republic of Iran Air Force.
Other countries that used F-4Es include: Egypt, Greece, Australia, and Germany.
The F-4E is the most widely used Phantom of all Phantoms produced.

Development of F-4B for US Navy, with AN/ASW-21 datalink communications equipment.
First flown on March 20, 1963.
In service over Vietnam with Squadron VF-213 from USS Kitty Hawk in spring of 1966.

The USAF's Wild Weasel programme concerns primarily with suppression of hostile weapon radar guidance systems.
The requirement for such a weapon system had been appreciated by Tactical Air Command as early as 1968, and feasibility studies were initiated in September that year, following which, eight sets of equipment were acquired for development, qualification testing and flight testing in two F-4D aircraft.
The F-4E however, was eventually chosen as the best aircraft on which to install the required equipment.
Equipment used for SEAD include the use of Westinghouse ECM pods in conjunction with AGM-45 Shrike anti-radiation missiles.
Modifications include the addition of a torpedo-shaped fairing to the top of the tailfin to carry APR-38 antennae, with other APR-38 antennae installed on the side of the fin and along the upper surface of the fuselage.
Other modifications include:

Changes to the LCOSS amplifier in the upper equipment bay
APR-38 CIS installation in the aft cockpit
APR-38 CIS installation in the forward cockpit
Associated with the APR-38 is a Texas Instruments computer, whose purpose is to accomodate varying future circumstances without demands for additional electronic hardware.
Removal of the M-61A1 gun system to allow sufficient room for installation of APR-38 subsystems (receiver, HAWC, CIS), and the provision of suitable cockpit displays.

The changes gave the F-4G Wild Weasel the capability to detect, identify and locate hostile electromagnetic emitters, and to deploy suitable weapons against them for their suppression or destruction.

The following descriptions applies to the F-4E:

Trailing-edge is a one-piece aluminium honeycomb structure.
Flaps and ailerons of all-metal construction, with aluminium honeycomb trailing-edges.
Inset ailerons limited to down movement only, the `up' function being supplied by hydraulically operated spoilers on upper surface of each wing.
Ailerons and spoilers fully powered by two independent hydraulic systems.

Two General Electric J79-GE-17A turbojet engines (each rated 79.6 kN; 17,900 lb st with afterburning).
Integral fuel tankage in wings, between front and main spars, and in seven fuselage tanks, with total capacity of 7,022 litres (1,855 US gallons; 1,545 Imp gallons).
Provision for one 2,270 litre (600 US gallon; 500 Imp gallon) external tank under fuselage and two 1,400 litre (370 US gallon; 308 Imp gallon) underwing tanks.

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 7,250 kg (16,000 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

DIMENSIONS:
Span:
C:	11.71 m	38 ft 5 in
E:	11.71 m	38 ft 5 in
Length:
C:	17.75 m	58 ft 3 in
E:	19.20 m	63 ft 0 in
Height:
C:	4.95 m	16 ft 3 in
E:	5.03 m	16 ft 6 in
Wing area:
C:	49.24 m²	530.0 sq ft
E:	49.24 m²	530.0 sq ft
WEIGHTS AND LOADINGS: F-4E:
Weight empty:	13,757 kg	30,328 lb
Weight empty, basic mission:	14,448 kg	31,853 lb
Combat T-O weight:	18,818 kg	41,487 lb
Design T-O weight:	26,308 kg	58,000 lb
Max T-O weight:	28,030 kg	61,795 lb
Max landing weight:	20,865 kg	46,000 lb
Max wing loading:	569.2 kg/m²	116.59 lb/sq ft
Max power loading:	176.1 kg/kN	1.73 lb/lb st
PERFORMANCE: (C: at 25,397 kg; 55,991 lb, E: at 28,030 kg; 61,795 lb T-O weight):
Max level speed with external stores:	over Mach 2.0
Average speed:
C:	506 kt	938 km/h; 583 mph
E:	496 kt	919 km/h; 571 mph
Stalling speed, approach power with BLC:
C:	151 kt	280 km/h; 174 mph
E:	158.6 kt	294.5 km/h; 183 mph
Max rate of climb at S/L:
C:	2,621 m/min	8,600 ft/min
E:	1,881 m/min	6,170 ft/min
Rate of climb at S/L, one engine out:
C:	1,591 m	5,220 ft/min
E:	1,067 m	3,500 ft/min
Service ceiling:
C:	10,620 m	34,850 ft
E:	8,565 m	28,100 ft
Service ceiling, one engine out:
C:	9,340 m	30,650 ft
E:	6,490 m	21,300 ft
T-O run:
C:	1,064 m	3,490 ft
E:	1,338 m	4,390 ft
Combat radius:
Area intercept:	683 n miles	1,266 km; 786 miles
Defensive counter-air:	429 n miles	795 km; 494 miles
Interdiction:	618 n miles	1,145 km; 712 miles
Ferry range:	1,718 n miles	3,184 km; 1,978 miles