Douglas DC-8
Illustrative image; it may differ from the actual aircraft.The Douglas DC-8 (sometimes McDonnell Douglas DC-8) is an early long-range narrow-body jetliner designed and produced by the American Douglas Aircraft Company. Work began in 1952 toward the United States Air Force's (USAF) requirement for a jet-powered aerial refueling tanker. After losing the USAF's tanker competition to the rival Boeing KC-135 Stratotanker in May 1954, Douglas announced in June 1955 its derived jetliner project marketed to civil operators. In October 1955, Pan Am made the first order along with the competing Boeing 707, and many other airlines soon followed. The first DC-8 was rolled out in Long Beach Airport on April 9, 1958, and flew for the first time on May 30.
Specifications
Figures for the DC-8-63 variant, the most representative of the family · it is 54% the length of a football pitch
The type first flew in 1958 (68 years ago) · About 556 units built · Production ended in 1972
Figures for the type, not for this particular aircraft: each variant and each configuration changes something. They are shown in both systems used in aviation.
The story of the type
Development
Background
At the end of World War II, Douglas was the dominant North American aircraft producer in the commercial aviation market. Douglas produced a succession of piston-engined aircraft (DC-2, DC-3, DC-4, DC-5, DC-6, and DC-7) through the 1930s, 1940s, and 1950s. While de Havilland flew the world's first jet airliner, the Comet, in May 1949, Douglas initially refrained from developing a jet airliner.
De Havilland's pioneering Comet entered airline service in May 1952. Initially, it appeared to be a success, but the Comet was grounded in 1954 after two fatal accidents which were subsequently attributed to rapid metal fatigue failure of the pressure cabin. Various aircraft manufacturers benefited from the findings and experiences gained from the investigation into Comet losses; specifically, Douglas paid significant attention to detail in the design of the DC-8's pressurized cabin. By 1952, Douglas had continued its success as a commercial aircraft manufacturer, having received almost 300 orders for its piston-engine DC-6 and its successor, the DC-7, which had yet to fly. The Comet disasters, and the airlines' subsequent lack of interest in jets, seemed to validate the company's decision to remain with propeller-driven aircraft, but its inaction enabled rival manufacturers to take the lead instead.
As early as 1949, rival company Boeing had started design work on a pure jet airliner. Boeing's military arm had experience with large long-range jets, such as the B-47 Stratojet and the B-52 Stratofortress strategic bombers. While producing and supporting these bombers for the United States Air Force (USAF), Boeing had developed a close relationship with the USAF's Strategic Air Command (SAC). The company also supplied the SAC's refueling aircraft, the piston-engined KC-97 Stratofreighters, but these proved to be too slow and low flying to easily work with the new jet bombers. The B-52, in particular, had to descend from its cruising altitude and then slow almost to its stall speed to refuel from the KC-97. Believing that a requirement for a jet-powered tanker was a certainty, Boeing started work on a new jet aircraft for this role that could be adapted into an airliner. As an airliner, it would have similar seating capacity to the Comet, but the use of a swept wing enabled a higher cruising speed and better range. First presented in 1950 as the Model 473-60C, Boeing failed to generate any interest from airlines, yet remained confident that the project was worthwhile and pressed ahead with a prototype, the Boeing 367-80 ("Dash-80"). After spending $16 million of its own money to build it, the Dash-80 rolled out on May 15, 1954.
Early design phase
During mid-1952, Douglas opted to covertly begin work on definition studies for a jet-powered transport aircraft. The company's design team examined various arrangements, including some that closely resembled the Comet. By mid-1953, the team had settled on a form similar to the final DC-8; an 80-seat, low-wing aircraft powered by four Pratt & Whitney JT3C turbojet engines, 30° wing sweep, and an internal cabin diameter of 11 feet (3.35 m) to allow five-abreast seating. The use of podded engines was seen as highly beneficial for maintenance purposes as well as to increase wing volume for accommodating fuel. The fuselage featured a double-bubble cross-section that produced relatively low drag while providing for a relatively spacious passenger cabin along with a large cargo deck that was sufficiently tall as to permit ground crews to stand up within it.
While Douglas remained lukewarm about the jet airliner project, it believed that the USAF tanker contract would go to two companies for two different aircraft, as several USAF transport contracts in the past had done. In May 1954, the USAF circulated its requirement for 800 jet tankers to Boeing, Douglas, Convair, Fairchild Aircraft, Lockheed Corporation, and Martin Marietta. At the time, Boeing was only two months away from having its prototype in the air. Just four months after issuing the tanker requirement, the USAF ordered the first 29 KC-135 Stratotankers from Boeing. Donald Douglas was reportedly shocked by the rapidity of the decision which, he claimed, had been made before the competing companies even had time to complete their bids. He protested to Washington, but without success.
Having already started on the DC-8 project, Douglas decided that the best option was to press on than abandon the project. Following consultations with the airlines, several design changes were made, such as the fuselage being widened by 15 inches (38 cm) to permit six-abreast seating, which in turn led to larger wings and tail surfaces being adopted along with a lengthening of the fuselage. The existence of the DC-8 was formally announced on June 7, 1955; at the time of the announcement, the development costs had been forecast to be roughly $450 million.
Variants
For domestic use, powered by 13,500 lbf (60.1 kN) Pratt & Whitney JT3C-6 turbojets with water injection. First Series 10 DC-8 flew on 30 May 1958. The initial DC-8-11 model had the original wingtips used on the prototype, and all remaining DC-8 Series 10 aircraft were upgraded to DC-8-12 standard. The DC-8-12 featured new low-drag wingtips and leading-edge slots, 80 inches (2.0 m) long between the engines on each wing and 34 inches (0.86 m) long inboard of the inner engines. These unique devices were covered by doors on the upper and lower wing surfaces that opened for low-speed flight and closed for cruise. The maximum weight increased from 265,000 to 273,000 pounds (120,200 to 123,830 kg). This model was originally named "DC-8A" until the series 30 was introduced. 30 DC-8-10s were built: 23 for United and six for Delta, plus the prototype. By the mid-sixties, United had converted 16 of its 21 surviving aircraft to DC-8-20 standard and the other five to -50s. Delta converted its six to DC-8-50s. The prototype was itself also converted to a DC-8-50.
It received FAA certification on August 31, 1958, entering service with United Airlines and Delta Air Lines on September 18, 1959.
Higher-powered 15,800 lbf (70.3 kN) thrust Pratt & Whitney JT4A-3 turbojets (without water injection) allowed a weight increase to 276,000 pounds (125,190 kg). 33 DC-8-20s were built plus 16 converted DC-8-10s. This model was originally named "DC-8B" but was renamed when the Series 30 was introduced.
The first Series 20 DC-8 flew on November 29, 1958 and received FAA certification on January 19, 1960.
For intercontinental routes, the three Series 30 variants combined JT4A engines with a one-third increase in fuel capacity and strengthened fuselage and landing gear. The DC-8-31 was certified in March 1960 with 16,800 lbf (74.7 kN) JT4A-9 engines for 300,000-pound (136,080 kg) maximum takeoff weight. The DC-8-32 was similar but allowed 310,000-pound (140,610 kg) weight. The DC-8-33 of November 1960 substituted 17,500 lbf (77.8 kN) JT4A-11 turbojets, a modification to the flap linkage to allow a 1.5° setting for more efficient cruise, stronger landing gear, and 315,000-pound (142,880 kg) maximum weight. Many -31 and -32 DC-8s were upgraded to this standard. A total of 57 DC-8-30s were produced (five of which were later upgraded to DC-8-50 standard).
The Series 30 DC-8 first flew on February 21, 1959 and received FAA certification on February 1, 1960.
The DC-8-40 was essentially the -30 but with 17,500 lbf (77.8 kN) Rolls-Royce Conway 509 turbofan engines for better efficiency, less noise and less smoke. The Conway was an improvement over the turbojets that preceded it, but the Series 40 sold poorly because of the traditional reluctance of U.S. airlines to buy a foreign product and because the still-more-advanced Pratt & Whitney JT3D turbofan was due in early 1961. The DC-8-41 and DC-8-42 had weights of 300,000 and 310,000 pounds (136,080 and 140,610 kg) respectively, the 315,000-pound (142,880 kg) DC-8-43 had the 1.5° flap setting of the -33 and introduced a 4% leading-edge wing extension to reduce drag and increase fuel capacity slightly – the new wing improved range by 8%, lifting capacity by 6,600 lb (3,000 kg), and cruising speed by better than 10 knots (19 km/h; 12 mph). It was used on all later DC-8s. The first DC-8-40 was delivered in 1960; 32 were built (of which three were eventually converted to DC-8-50s).
The Series 40 DC-8 first flew on July 23, 1959 and received FAA certification on 24 March 1960.
The definitive short-fuselage DC-8 came with the same engine that powered the vast majority of 707s, the JT3D. Twenty earlier DC-8s were converted to this standard. All but the -55 were certified in 1961. The DC-8-51, DC-8-52 and DC-8-53 all had 17,000 lbf (75.6 kN) JT3D-1 or 18,000 lbf (80.1 kN) JT3D-3B engines, varying mainly in their weights: 276,000 pounds (125,190 kg), 300,000 pounds (136,080 kg) and 315,000 pounds (142,880 kg) respectively.
Overview and history adapted from Wikipedia (CC BY-SA) · technical figures from the manufacturer’s published specifications and standard aviation references
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BibTeX
@misc{vuelopedia_en_model_dc8,
author = {{Vuelopedia}},
title = {{Douglas DC-8}},
publisher = {Fundación Poderia},
year = {2026},
date = {2026-10-10},
url = {https://vuelopedia.org/en/model/dc8},
howpublished = {\url{https://vuelopedia.org/en/model/dc8}},
urldate = {2026-10-16},
note = {Accessed 2026-10-16}
}Wikipedia
{{cite web |url=https://vuelopedia.org/en/model/dc8 |title=Douglas DC-8 |website=Vuelopedia |publisher=Fundación Poderia |date=2026-10-10 |access-date=2026-10-16 |language=en}}