McDonnell Douglas F-4 Phantom II (2024)

McDonnell Douglas F-4 Phantom II (1)

The Phantom II was the first fighter aircraft to be designed with missiles only. Guns were added on later models.

The design of the Phantom II, headed by Herman Barkey, was initiated in September 1953 as the A-H1 (Model 98), resulting from several studies aimed to extend the production and performance of the F-3H Demon. After losing out to the Grumman XF9F-9 Tiger and Chance Vought XF8U-1 Crusader in 1953, McDonnell persisted and the US Navy requested from McDonnell, two YA-H1s (Model 98B) on October 18, 1954.3 After seven months of evaluation, the Navy requested on May 26, 1955 that the two YA-H1s be changed from twin-engine, cannon-armed, all-weather single-seat fighters, to all-weather two-seat, missile armed interceptors, without cannons. The primary armament would be four Sparrow III radar-guided missiles mounted in semi-submerged slots beneath the fuselage with a Westinghouse vacuum-tube AN/APQ-50 airborne-interception 24" radar set. Specifications also required patrolling for two hours at a distance of 250 nautical miles (465 km) from a carrier, and staying aloft for two deck cycles (three hours) without air refueling.4 McDonnell was able to meet the new requirements and the aircraft was given a new designation, F4H-1.5 Five pre-series aircraft were also requested, which was increased to 21 F4H-1s (F-4A) on December 19, 1956, and then again to 45 aircraft on December 17, 1958. Its maiden flight was on May 27, 1958 and by December 6, 1959 it would set its first world record by achieving an altitude of 98,556 ft (30,040 m),6 and on December 5, 1961 set a new record for a sustained altitude at 66,443.8 ft (20,251 m) over a 25 km course.7

Before production began, extensive wind tunnel testing revealed stability problems above Mach 2 and numerous design changes would be made to become the now familiar F-4 Phantom. The wing was originally designed with a 45 degree sweepback with a constant anhedral, but it was found that a three degree dihedral was needed to improve stability.8 Rather than design a new wing requiring major modifications, outer wing panels were added with a twelve degree dihedral.9 The 12 degree panel corresponds to a 3 degree dihedral overall. This became one of the F-4 Phantom's most distinguishing features, which incorporated a dog-tooth leading edge and drooping ailerons or flaperon—flaperons move down only, not up. Ahead of each flaperon were spoilers, which aided in lateral control.The YF4H-1 was fitted with wing leading edge flaps which extended from the wingtip all the way inward to about one-quarter span. There were two segments with the division at the wing folding point. The leading edge flaps would extend on landing to provide additional lift at low speeds. The tailplane was a one-piece stabilator, requiring 23-1/2 degree anhedral that placed it away from wing downwash at high speeds,10 The J79-GE-8 was delayed coming into use and the J79-GE-3A turbojet with 9,600 lb. s.t. and 14,800 lb s.t. with afterburner (w/ab) was used in May 1958.

McDonnell Douglas F-4 Phantom II (2)

McDonnell Douglas F-4A Phantom II

F-4A (F4H-1F) changes were a leading edge flap boundary layer air control system first used on the 5th preproduction aircraft and blown flaps introduced on the 7th preproduction aircraft.11 The wing leading edges and trailing edge flaps were blown by high-pressure bleed air from the engine compressors, which produced a thin layer of air which helped keep airflow attached at high angles of attack. Originally fixed geometry inlet cheeks were placed on the fuselage to provide smooth inlet air flow, but this was changed to a two-piece configuration with forward variable ramps that were controlled by an air data computer. On the 19th aircraft, the canopy was redesigned to improve visibility and a bulbous radome was installed to accommodate the a new larger 32" radar dish for the AN/APQ-72 air intercept radar as well as under nose bulge for infra-red heat seeking equipment creating a droop nose effect. Provisions were provided for six Sparrow III air-to-air missiles under the wings and fuselage. For air-to-ground missions, the aircraft was capable of carrying 16,000 lb of ordinance on four underwing pods and one centerline station or a single nuclear weapon. In place of ordinance, external fuel could be carried in three tanks and a retractable in-flight refueling probe was installed on the forward starboard fuselage. Twenty-three preproduction aircraft were given the J79-GE-2 or -2A with 10,350 lb s.t. (16,150 lb s.t. w/ab) which was replaced on later F-4As with J79-GE-8s, bringing the aircraft to almost full F-4B standards.12

McDonnell Douglas F-4 Phantom II (3)

The McDonnell Douglas F-4B Phantom was the first major production type.

F-4Bs (F4H-1) were the first major production type with construction beginning in 1961 for 192 aircraft. 13 It was given the AN/APQ-72 air intercept radar and used AAA-4 infrared sensor beneath the nose radome. Missile combinations were six Ratheon Sparrow IIIs or four Sparrow IIIs with four GE/Philco sidewinder air-to-air missiles (AAM) mounted on two wing pylons and in four semi-recessed under fuselage bays. For the attack role, the F-4B could accommodate four wing and one fuselage attach points for a total of 16,000 lb of assorted bombs, including nuclear, conventional, napalm, missiles, rockets or three fuel tanks in place of weapons. It was given the J79-GE-8 turbojet engine with 10,900 lb s.t. (17,000 lb s.t. w/ab). In naval service, the F-4Bs were progressively upgraded as a result on combat experience in Vietnam. Chaff dispensers were added and Electronic Counter Measures (ECM) were improved with the addition of Radar Homing and Warning Systems (RHAWS) and Deception Systems (AN/ALQ-51 and AN/ALQ-100). The tailplane was retrofitted with slotted stabilizers as on the "J" models to reduce landing speeds. Production of the F-4B ended in 1967 with the completion of 649 aircraft.14 Forty-six unarmed photo-reconnaissance versions were designated as the RF-4B, of which all 46 were procured by the USMC. 228 F-4Bs were upgraded in 1972 and were designated as the F-4N.

F-4Cs (F-110A) entered service with the 4453rd Combat Crew Training Wing at MacDill AFB in November 1963. First designated as the F-110A with the name Spectre, then as the F-4C, as the USAF was reluctant to acquire the Navy F-4 Phantom II. However, it quickly became the largest F-4 operator after it was pressured by Defense Secretary Robert S. McNamara to evaluate it against the Convair F-106A. McNamara wanted to reduce defense expenditures by standardizing Armed Forces equipment and in January 1962, the Department of Defense (DoD) instructed McDonnell to deliver two F4H-1s to Langley AFB in Virginia for evaluation. The aircraft were painted in TAC markings with F-110A painted very prominently on the nose. Compared to the F-106, it was capable of carrying heavier loads, had a 25% greater radar range, and required 1/3 less maintenance man-hours to flight-hours. It was considered much more versatile than the Republic F-105 Thunderchief and demonstrated better air superiority because of its lower wing loading and higher power ratings. For the reconnaissance role, it could be fitted for night photographic operations, unlike the RF-101 Voodoo.

McDonnell Douglas F-4 Phantom II (4)

First designated as the F-110A then as the F-4C, the USAF was reluctant to acquire the Navy F-4 Phantom. However, it would become the largest F-4 operator.

Externally the F-4C was very similar to F-4B, except the C model had wider tires requiring a bulging fairing for the tires. This feature was added to all models as weight increased. Internal differences were dual controls in the rear co*ckpit, the refueling receptacle was moved to the top of the fuselage and it had substantially different electronic equipment. Electronics included AN/APQ-100 radar, AN/APA-157 radar set group, AN/AJB-7 bomb control system, AN/ASN-48 Inertial Navigation System (INS) and an AN/ASN-46 navigation computer. The F-4C had no internal guns, but was basically armed with four AIM-7 Sparrow air-to-air missiles (AAM) recessed beneath the fuselage. External stores were conventional, chemical, laser, nuclear bombs or AAM, AGM, rocket launchers, SUU-16/A or SUU-23/A gun pods, or mines for a maximum load of 16,000 lb. The F-4C was powered by two J79-GE-15 turbojet engines with 10,900 lb s.t. (17,000 lb s.t. w/ab) with a built-in cartridge starting system. Delivery began in November 1963 and production ended in February 1967 with the completion of 583 aircraft. Forty of these aircraft were transferred to Spain and others became EF-4Cs.

The F-4E was the major USAF variant with 959 aircraft produced for the USAF and 428 produced for export. Although the original Model 98B proposed four 20-mm cannons, a design change in 1954 called for a long-range high-altitude Mach 2 interceptor of which only missiles would be required.15 However, experience in Vietnam with air-to-air encounters showed that this arrangement was inadequate since the earlier Sparrow and Sidewinder missiles did not perform up to expectations. They frequently missed their targets and were subject to countermeasures. SUU-16 gun pods were installed on the F-4C but the extra drag degraded performance and took the place of ordinance or fuel pods. To correct this, an internal General Electric Vulcan (M61A) 20 mm, six-barrel, rotary-cannon with 639 rounds was installed on the F-4E. Due to limited space, a new nose configuration was adopted from the RF-4C reconnaissance version, housing an AN/APQ-120 radar set with a smaller 24.5" x 27.4" antenna and an external pod below the nose housed the cannon.16 Other modifications included a slotted stabilizer, the removal of the automatic wing folding mechanism, a ninety-five gallon fuel tank was installed in the aft fuselage to balance the cannon, and self-sealing fuel tanks replaced fuel bladders. A blast diffuser and derichment system was installed to prevent the ingestion of gas gun vapors which would cause the engine to flame-out. Late model F-4Es included a beefed-up wing center section to extend service life and leading edge slats to improve flight performance. Early F-4Es were later retrofitted with the leading edge flap systems.

McDonnell Douglas F-4 Phantom II (5)

The McDonnell Douglas F-4E Phantom was the major USAF variant and had a an internal rotary-cannon.

The basic armament still included four semi-recessed AIM-7 AAM and external stores of earlier variants but export version were delivered without the ability of arming and delivering nuclear weapons.17 As new electronics became available they were added during production or later retrofitted with AVQ-23A/B Pave Tack range finder, AN/AVQ-26 Pave Tack infrared/laser target designator and AN/ASX-1 target identification system. 180 F-4Es were later retrofitted with a Lear Siegler AN/ARN-101(V) to improve navigation and accuracy of weapons delivery. The F-4E was powered by two J79-GE-17 turbojet engines with 11,870 lb s.t. (17,900 lb s.t. w/ab) and later modifications included smokeless burner cans which reduced the black smoke trail which made the aircraft easier to spot from a distance. Export versions of the F-4E went to Israel, Turkey, Greece, Iran and Korea. 116 F-4Es were modified in 1975 and adapted as electronic warfare systems which were redesignated as the F-4G Wild Weasel.

The F-4J superseded the F-4B and was the last version to be produced for both the US Navy and USMC. It was equipped with a ground attack AN/AJB-7 bombing system, increasing that capability substantially over the F-4B. Also installed was an AN/AWG-10 fire control system housed in an enlarged radome, an AN/APG-59 pulse-doppler radar to detect aircraft at low altitudes and an AN/ASW-25 one-way data link system for automatic carrier landings. Other changes included larger wheels and the stronger wing center section as on the USAF version, an additional fuel cell in the rear fuselage, and (VTAS) Visual Target Acquisition System helmet sight, which was also retrofitted on earlier models. The F-4J was powered by two J79-GE-10 turbojet engines with 11,870 lb s.t. (17,900 lb s.t. w/ab.) Armament included four semi-recessed AIM-7 AAM plus external stores of16,000 lb of bombs, missiles or rockets.

The F-4M was the RAF version of the Royal Navy F-4K, both of which were powered by the two Rolls-Royce RB.168-25R Spey turbofan engines with 12,250 lb s.t. (20,515 lb s.t. w/ab).18 Changes were made to the fuselage to adapt the new engine and the engine inlets were larger, but in spite of the increase in power, performance was degraded. The RAF version was equipped with an AN/AWG-12 fire control system and a Ferranti INS. Basic armament was four Sparrow AAM, but later replaced with British Aerospace Sky Flash missiles. The reconnaissance version carried a special pod that housed cameras, infrared sidescan and side-looking radar. 116 F-4Ms were produced between July 1968 and October 1969.

The F-4 Phantom was first in many aerospace innovations. One system introduced in 1959 was the buddy tank inflight refueling system which was tested successfully at supersonic speeds and new weapons were tested such as the GE/Philco AAM-N-7 sidewinder missile. It was able to attain an initial climb of 35,000 ft/min and was able to carry an external bomb load of no less than 22,500 lb. It was truly a remarkable airplane.

The F-4 Phantom would break fifteen aviation world records listed below.
1. December 6, 1959. Absolute altitude record of 98,556 ft (30,040 m). 2. September 5,1960. Attained and average speed of 1,958 mph over a triangular course for 15 min and 91 sec. 3.September 25,1960. 100 km closed circuit speed record of 1,390 mph (Mach 2) with a continuous sustained turn of 3Gs.19 4.May 24,1961. Ontario, CA to Brooklyn, NY (Floyd Bennett), 2 hr 47 min, @ average speed of 870 mph. 2,446 miles (3,936 km). 5.August 28,1961. Low altitude record of 125 ft (38 m) at 902 mph (1,452 km) for 1.86 miles (3 km). 6.December 5,1961. Sustained altitude record of 66,443 ft (20,252 m). 7.February 21,1962. Time to height record. 9,843 (3,000 m) in 34.52 sec. 8.February 21,1962. Time to height record. 19,685 (6,000 m) in 48.78 sec. 9.March 1,1962. Time to height record. 29,528 (9,000 m) in 61.62 sec. 10.March 1,1962. Time to height record. 39,370 (12,000 m) in 77.15 sec. 11.March 1,1962. Time to height record. 49,213 (15,000 m) in 114.54 sec. 12.March 31,1962. Time to height record. 65,617 (20,000 m) in 178.50 sec. 13.April 3,1962. Time to height record. 82,021 (25,000 m) in 230.44 sec. 14.April 4,1962. Time to height record. 98,425 (30,000 m) in 371.43 sec. 15.April 4,1962. Absolute altitude record of 100,000 ft (30,480 m). Not officially recorded by the FIA.
Powerplant Armament F-4B Two General Electric J79-GE-8A/-8B/-8C
10,900 lb s.t. (4,944 kg)17,000 lb s.t. ab (7,711 kg)
Six or eight air-to-air missiles,
16,000 lb (7,257 kg) bombs/rockets
RF-4C Two General Electric J79-GE-15
10,300 lb s.t. (4,672 kg)17,000 lb s.t. ab (7,711 kg)
None F-4E Two General Electric J79-GE-17
11,870 lb s.t. (5,384 kg)17,900 lb s.t. ab (8,119 kg)
One 20 mm rotary cannon,
16,000 lb (7,257 kg) missiles/bombs/rockets
F-4J Two General Electric J79-GE-8B/-8C/-10
10,900 lb s.t. (4,944 kg)17,900 lb s.t. ab (8,119 kg)
Four air-to-air missiles,
16,000 lb (7,257 kg) missiles/bombs/rockets
F-4M Two Roll-Royce Spey RB-168-25R Mk 202/203
12,250 lb s.t. (5,556 kg)20,515 lb s.t. ab (9,305 kg)
Four British Aerospace Sky Flash air-to-air missiles
16,000 lb (7,257 kg) missiles/bombs/rockets
McDonnell Douglas F-4 Phantom II (2024)
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