McDonnell F-4 Phantom II

Summary

Category	Combat aircraft
Origin country	🇺🇸 United States
First flight	27 May 1958
Year of introduction	1962
Number produced	5195 units
Average unit price	$3 million

Description

In 1952, McDonnell began initial studies for a new aircraft. By 1953, McDonnell Aircraft began revising its F3H Demon naval fighter, proposing the "Super Demon" (F3H-G/H) to the US Navy. On 18 October 1954, the design was reworked into an all-weather fighter-bomber, and the company received a letter of intent for two YAH-1 prototypes. On 26 May 1955, the project's requirement shifted to that of an all-weather fleet defense interceptor, necessitating the addition of a second crewman to operate the radar. The XF4H-1 was designed to carry four semi-recessed AAM-N-6 Sparrow III radar-guided missiles and be powered by two J79-GE-8 engines. On 25 July 1955, the Navy ordered two XF4H-1 test aircraft and five YF4H-1 pre-production examples. The aircraft was given the name "Phantom II", referencing the earlier McDonnell FH-1 Phantom. The Phantom made its maiden flight on 27 May 1958. On 17 December 1958, the F4H was declared the winner of the competition. In 1959, the Phantom began carrier suitability trials, with the first complete launch-recovery cycle performed on 15 February 1960 from USS Independence. The aircraft was briefly designated F-110A and named "Spectre" by the USAF. The Tri-Service aircraft designation system designation, F-4, was adopted in September 1962. A total of 5,195 Phantoms were built from 1958 to 1981.

The F-4 Phantom is a tandem-seat fighter-bomber, initially designed as a carrier-based interceptor for the U.S. Navy. Later variants, such as the F-4F, incorporated pulse-Doppler radar and extensive use of titanium in the airframe. Despite a maximum takeoff weight exceeding 60,000 lb (27,000 kg), the F-4 demonstrated a top speed of Mach 2.23 and an initial climb rate exceeding 41,000 ft/min (210 m/s). The thin-section wing had a leading-edge sweep of 45° and was equipped with blown flaps for enhanced low-speed handling and a distinctive "dogtooth" for improved control at high angles of attack. To avoid redesigning the titanium central section, the outer portions of the wings were angled upwards by 12°, achieving an effective 5° dihedral over the entire wingspan after wind tunnel testing revealed lateral instability. The air intakes were equipped with one fixed ramp and one variable geometry ramp with angle scheduled to maximize pressure recovery between Mach 1.4 and Mach 2.2.

The F-4 Phantom was designed with nine external hardpoints, capable of carrying a payload of up to 18,650 pounds (8,480 kg) of weapons. This ordnance load includes air-to-air missiles such as the AIM-9 Sidewinder and AIM-7 Sparrow, air-to-ground missiles such as the AGM-65 Maverick, and various bombs including general-purpose, cluster, and guided weapons. The aircraft was also capable of carrying thermonuclear weapons. Originally designed without an internal cannon, some later models, such as the F-4E, incorporated an internally mounted 20 mm M61 Vulcan cannon with 640 rounds.

The F-4 Phantom was employed extensively during the Vietnam War, initially serving as the principal air superiority fighter for the U.S. Air Force, Navy, and Marine Corps, with later roles expanding to include ground-attack and aerial reconnaissance. All five American servicemen who achieved ace status during this conflict did so while flying F-4s. The Phantom participated in the 1991 Gulf War performing reconnaissance and Wild Weasel missions before officially retiring from combat service in 1996. The F-4 was the only aircraft type used by both U.S. flight demonstration teams: the United States Air Force Thunderbirds (F-4E) and the United States Navy Blue Angels (F-4J). Beyond the U.S., the F-4 was operated by the armed forces of 11 other nations. Israeli Phantoms engaged in extensive combat in various Arab–Israeli conflicts. Iran utilized its Phantoms during the Iran–Iraq War after acquiring a substantial fleet. As of the current date, the F-4 continues in active service with the air forces of Iran, Greece, and Turkey, including recent deployments against the Islamic State group in the Middle East.

Main Variants:

F-4A: Initial USN version, designated F4H-1 before 1962, used primarily for testing and training.
F-4B: First definitive Phantom for the USN and USMC, equipped with Westinghouse APQ-72 radar and powered by J79-GE-8 engines.
F-4C: USAF's version of the Phantom, adapted for both air-to-air and air-to-ground roles.
F-4J: Improved variant with J79-GE-10 engines and the Westinghouse AN/AWG-10 Fire Control System providing look-down/shoot-down capability.
F-4E: This variant featured an internal M61 Vulcan cannon and was widely produced for both the U.S. Air Force and export.

Technical specifications

Version: F-4E
Crew	1 pilot + 1 WSO
Operational range	680 km (423 mi)
Maximum speed	2370 km/h (1473 mph)
Wing area	49.2 m² (529.6 sqft)
Wingspan	11.7 m (38.4 ft)
Height	5 m (16.4 ft)
Length	19 m (62.3 ft)
Service ceiling	18288 m (60000 ft)
Empty weight	13757 kg (30329 lbs)
Max. takeoff weight	28030 kg (61795 lbs)
Climb rate	210.0 m/s (689.0 ft/s)
Takeoff distance	1370 m (4495 ft)
Powerplant	2 × turbojets General Electric J79-GE-17A delivering 8093 kgp
Ejection seat	Martin-Baker Mk 7