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The Avro 706 Ashton was a British prototype jet airliner made by Avro during the 1950s. Although it flew nearly a year after the de Havilland Comet, it represented an experimental programme and was never intended for commercial use. The Avro 689 Tudor 9 was based on the Avro 689 Tudor II piston-engined airliner using experience on work on the Rolls-Royce Nene jet-powered experimental variant, the Tudor 8, which made its first flight on 6 September 1948. The Avro Type 689 Tudor 9, later renamed the Avro 706 Ashton, was a four-jet-engined research aeroplane powered by Rolls-Royce Nene engines paired in wing nacelles. Six were built using the Tudor airframe, beginning with the conversion of Tudor I initially powered by Nene 5 engines. The Ashtons that followed incorporated the upgraded Nene 6 and featured an enlarged, "square-shaped" tail fin and tricycle landing gear replacing the original "taildragger" configuration. The engines were tightly grouped in two nacelles that were faired neatly into the wing but also extended below in streamlined pods. The four-engine arrangement compensated for the low thrust of the early jet engines and greatly reduced asymmetric effects in an "engine-out" scenario. The crew was composed of a pilot, co-pilot, navigator, flight engineer and radio operator clustered together in the cockpit and front compartment of the Ashton. A larger complement could be carried in the spacious fuselage when warranted.

The Fiat G.55 Centauro (Italian: "Centaur") was a single-engine single-seat World War II fighter aircraft used by the Regia Aeronautica and the Aeronautica Nazionale Repubblicana in 1943–1945. It was designed and built in Turin by Fiat. The Fiat G.55 was arguably the best type produced in Italy during World War II, (a subjective claim also frequently made for the Macchi C.205 Veltro as well as for the Reggiane Re.2005 Sagittario) but it did not enter production until 1943, when, after comparative tests against the Messerschmitt Bf 109G and the Focke-Wulf Fw 190, the Luftwaffe itself regarded the Fiat G.55 as "the best Axis fighter". During its short operational service, mostly under the Repubblica Sociale Italiana insignia, after the 8 September 1943 armistice, this powerful, robust and fast aircraft proved itself to be an excellent interceptor at high altitude. In 1944, over Northern Italy, the Centauro clashed with British Supermarine Spitfire, P-51 Mustang, P-47 Thunderbolt and P-38 Lightning, proving to be no easy adversary. Italian fighter pilots liked their Centauro but by the time the war ended, fewer than 300 had been built. By comparison, the Germans produced 35,000 Bf 109s. By 1939, all the main Italian aircraft factories had begun designing a new series of monoplane fighter aircraft, using inline engines as opposed to the radial engines that powered the first generation Italian monoplane fighters used in the early years of World War II (fighters such as the Fiat G.50 and the Macchi C.200). This process saw the first generation radial-engined fighters re-equipped with the Italian-built copy of the Daimler-Benz DB 601 engine, the so-called Serie 1/2, whose most prominent representative was the Macchi C.202 Folgore (which was an aerodynamically revised Macchi C.200- also known as Macchi C.201 - with an inline V-12 instead of a radial engine). Aircraft in this series were given alphanumeric designations ending in the number "2". However, the process didn't stop, and already in 1941, designers shifted their attention on the new, larger and more powerful Fiat RA.1050, a license-built copy of the Daimler-Benz DB 605. Aircraft powered by this new engine became the "Serie 5", and all had alphanumeric designations ending in the number "5" (Macchi C.205, Reggiane Re.2005, Fiat G.55). Fiat designer Giuseppe Gabrielli, while experimenting a new version of his Fiat G.50 fighter, equipped with the DB 601, started a new design that was to be powered by the DB 605. The first G.55 prototype flew on 30 April 1942, piloted by commander Valentino Cus, immediately showing its good performance and flight characteristics. It was armed with one 20 mm MG 151/20 cannon with 200 rounds of ammunition, installed in the forward fuselage and firing between the cylinder banks, exiting through the propeller hub. In "Sottoserie O" airframes, there were also four 12.7 mm (.5 in) Breda-SAFAT machine guns; two in the upper engine cowling, and two in the lower cowling, firing through the propeller arc, with 300 rpg. This layout soon proved to be troublesome, both for rearming and for the servicing of the lower cowling mounted machine guns: for this reason, the two lower machine guns were removed, and replaced with a 20 mm MG 151/20 in each wing, in the later production series, the Serie 1 (for a total of three cannon and two 12.7mm machine guns, although this varied; some had machine guns in the wings instead of cannon). For further details, including operational history, further development and variants, click here.

The Short S.17 Kent was a British four-engined 15-seat biplane luxury flying boat airliner, designed and built by Shorts to meet a requirement from Imperial Airways for an aircraft with greater range than the Short Calcutta. The new aircraft was to have sufficient range to fly the stage from Mirabella, Crete, to Alexandria in Egypt without the need for refuelling stops in Italian colonial territory due to a political row which had led the Italian Government to ban British aircraft from its ports. Three aircraft were built, each receiving its own name: Scipio, Sylvanus and Satyrus; they were referred to collectively within Imperial Airlines as the Scipio Class flying boats. Each had an aircrew of three (two pilots and a radio operator/navigator) and a steward to prepare meals and light refreshments for the passengers. The Short Kent flying boat was essentially an enlarged, four-engined version of the Calcutta, with the same passenger carrying capacity but with an increased payload for mail and fuel. It was powered by four Bristol Jupiter XFBM radial engines mounted on vertical struts between the upper and lower planes. The wings were constructed using corrugated duralumin box spars and tubular rib assemblies, with a fabric covering and Frise ailerons on the upper and lower wings. Duralumin walkways were provided to allow ready access to the engines for maintenance purposes. The tail unit consisted of braced monoplane horizontal and vertical stabilizers; the tailplane was fitted with Flettner-type servo tabs for trimming on the Short Scylla which had the same wings and tail as the Kent. The anodised duralumin fuselage was mounted below the lower wing, with the planing bottom of the hull made of stainless steel (as on the Singapore II) with a transverse main step. The use of stainless steel reduced the frequency of land inspections of the hull. The bimetallic corrosion problems experienced on the Singapore II hull had been solved; Short Brothers became the first company to master the technique of building seaplane floats and flying boat hulls in this combination of metals. A quick-release hook (controlled by the pilots) was provided, which enabled the captain to start, warm up and (when required) run all four engines up to full power for takeoff while the aircraft was still attached to the mooring buoy. Maximum comfort was required for passengers and crew: the Kent's passenger cabin was 8 ft 6 in (2.59 m) wide and 14 ft (4.27 m) long. The seating was arranged in four rows of facing pairs, with a centre aisle, Pullman-style. The steward's pantry, situated on the port side aft of the passenger cabin, was equipped with twin-burner oil stoves on which stewards (and the valets of valued passengers) could cook meals in flight. The toilet and washroom were opposite the pantry; the mail and freight compartment was further aft. Special attention was paid to sound levels in the passenger cabin and crew's stations; accordingly the engines were fitted with exhaust collector rings and long tailpipes, to reduce exhaust noise inside the hull. The cockpit, for two pilots, was fully enclosed (unlike that of the Calcutta's) with a separate Radio Officer's station directly aft of the cockpit. Three units were built.

The ShinMaywa US-2 is a large Japanese short takeoff and landing amphibious aircraft that employs boundary layer control technology for enhanced STOL and stall suppression performance. Manufactured by seaplane specialist ShinMaywa (formerly Shin Meiwa), it was developed from the earlier Shin Meiwa US-1A seaplane, which was introduced during the 1970s. The ShinMaywa US-2 was developed on behalf of the Japan Maritime Self-Defense Force (JMSDF) as a 'like-for-like' replacement for its aging US-1A fleet. In Japanese service, it is operated in the air-sea rescue (ASR) role. The US-2 can also be used in other capacities, such as an aerial fire fighter, carrying 15 tonnes of water for this mission. Various overseas operators have held discussions on potential acquisitions of the type, including the Indian Navy and Indian Coast Guard. Other countries such as the United States, Indonesia, Thailand, and Greece have also shown interest in the US-2 for various purposes. During 1969, the Japan Maritime Self-Defense Force (JMSDF) issued a production order to Japanese seaplane manufacturer Shin Meiwa for a group of 21 anti-submarine aircraft, which were given the designation PS-1. The service had also opted to procure a variant of the type, designated US-1A, specifically for search-and-rescue (SAR). The US-1A was Japan's first amphibian - capable of being used on land and sea. During the 1990s when the US-1A fleet was beginning to show its age, the JMSDF attempted to obtain funding towards acquiring a replacement, but could not secure enough to develop an entirely new aircraft. Therefore, during 1995, ShinMaywa, as Shin Meiwa had been renamed (reportedly so that the name would be easier to pronounce for non-Japanese speakers) commenced work on a project to develop an upgraded and modernised version of the US-1A, initially referred to as the US-1A kai (US-1A 改 - meaning "improved US-1A"). This modified aircraft features numerous aerodynamic refinements over its predecessor, along with a pressurised hull, and the adoption of more powerful Rolls-Royce AE 2100 engines and electronic cockpit instrumentation. The JMSDF also listed various refinements for the amphibian, including improved handling while landing on water, better onboard patient transfer facilities, and improved search-and-rescue capabilities at sea. On 18 December 2003, flight testing of the type, which was subsequently designated as the US-2, commenced. During early 2007, ShinMaywa formally launched commercial production of the amphibian. Production is handled by several of Japan's aviation companies. Mitsubishi manufactures the outer wing sections and the rear part of the engine nacelles, while NIPPI Corporation builds the watertight landing gear housings, and Kawasaki Heavy Industries produces the cockpit. Final assembly is performed by ShinMaywa around the US-2's hull. The production line only has the capacity to produce two aircraft at a time. During 2009, the first production US-2, which was outfitted for the search and rescue mission, was delivered to the Japan's Ministry of Defense. In 2010, ShinMaywa unveiled specifications for a civil fire-fighting variant of its US-2 amphibian. It began marketing the new variant to potential overseas customers that same year. The fire-fighting model replaces one fuel tank with a 15 tonne water tank, reducing its maximum range to 2,300 km (1,245 nm) compared with the SAR's 4,700 km range. The tank is durable enough for salt water, foam and fire retardant. Other features include a pair of water scoops for collecting water, automatic foam mixing equipment and a computer-controlled water drop system.

The Fairey Hendon was a British monoplane, heavy bomber of the Royal Air Force, designed by Fairey Aviation in the late 1920s. The aircraft served in small numbers with one squadron of the RAF between 1936 and 1939. It was the first all-metal construction low-wing monoplane to enter service with the RAF. The Hendon was built to meet the Air Ministry Specification B.19/27 for a twin-engine night bomber to replace the Vickers Virginia, competing against the Handley Page Heyford and Vickers Type 150. The specification required a range of 920 mi (1,480 km) at a speed of 115 mph (185 km/h), with a bomb load of 1,500 lb (680 kg). To meet this requirement, Fairey designed a low-winged cantilever monoplane with a fixed tailwheel undercarriage. The fuselage had a steel tube structure with fabric covering with a pilot, a radio operator/navigator and three gunners, in open nose, dorsal and tail positions. Bombs were carried in ten large and six smaller bomb cells in the fuselage and wing centre section between the engines. Variants powered by either radial engines or liquid-cooled V12 engines were proposed. The prototype K1695 (which was known as the Fairey Night Bomber until 1934) first flew on 25 November 1930, from Fairey's Great West Aerodrome in Heathrow and was powered by two 460 hp (340 kW) Bristol Jupiter VIII radial engines. The prototype crashed and was severely damaged in March 1931 and was rebuilt with two Rolls-Royce Kestrel VI engines. After trials, 14 production examples named the Hendon Mk.II were ordered. These were built by Fairey's Stockport factory in late 1936 and early 1937 and flown from Barton Aerodrome, Manchester. Orders for a further sixty Hendons were cancelled in 1936, as the prototype of the first of the next generation of British heavy bombers—the Armstrong Whitworth Whitley—had flown and showed much higher performance. The Hendon Mk.II was powered by two Rolls-Royce Kestrel VI engines. The production Hendon Mk.II included an enclosed cockpit for the pilot and navigator. The type was delayed by the crash and a rebuild of the prototype and the Heyford received the majority of the orders to replace RAF heavy bombers, the Hendon coming into service three years later. The only Hendon-equipped unit, 38 Squadron, began operational service at RAF Mildenhall in November 1936, replacing Heyfords, later moving to RAF Marham, Norfolk. Later, the Hendons went to 115 Squadron, which was formed from 38 Squadron. The type was soon obsolete and replaced from late 1938 by the Vickers Wellington. By January 1939, the Hendons had been retired and were then used for ground instruction work, including the radio school at RAF Cranwell. Variants Hendon Mk.I Prototype, one built Hendon Mk.II Production variant with two Rolls-Royce Kestrel VI engines, 14 built

The Sukhoi Su-24 (NATO reporting name: Fencer) is a supersonic, all-weather tactical bomber developed in the Soviet Union. The aircraft has a variable-sweep wing, twin engines and a side-by-side seating arrangement for its crew of two. It was the first of the USSR's aircraft to carry an integrated digital navigation/attack system. The Su-24 started development in the early 1960s and entered full production in 1967. Production ceased in 1993. It remains in service with the Russian Aerospace Forces, Syrian Air Force, Ukrainian Air Force, Algerian Air Force and various other air forces to which it was exported. The Su-24 has a shoulder-mounted variable geometry wing outboard of a relatively small fixed wing glove, swept at 69°. The wing has four sweep settings: 16° for takeoff and landing, 35° and 45° for cruise at different altitudes, and 69° for minimum aspect ratio and wing area in low-level dashes. The variable geometry wing provides excellent STOL performance, allowing a landing speed of 230 kilometers per hour (140 mph), even lower than the Sukhoi Su-17 despite substantially greater takeoff weight. Its high wing loading provides a stable low-level ride and minimal gust response. The Su-24 has two Saturn/Lyulka AL-21F-3A afterburning turbojet engines with 109.8 kN (24,700 lbf) thrust each, fed with air from two rectangular side-mounted intakes with splitter plates/boundary-layer diverters. In early Su-24 ("Fencer A" according to NATO) aircraft these intakes had variable ramps, allowing a maximum speed of 2,320 kilometers per hour (1,440 mph), Mach 2.18, at altitude and a ceiling of 17,500 meters (57,400 ft). Because the Su-24 is used almost exclusively for low-level missions, the actuators for the variable intakes were removed to reduce weight and maintenance. This has no effect on low-level performance, but absolute maximum speed and altitude are cut to Mach 1.35 and 11,000 meters (36,000 ft). The earliest Su-24 had a box-like rear fuselage, which was soon changed in production to a rear exhaust shroud more closely shaped around the engines to reduce drag. The revised aircraft also gained three side-by-side antenna fairings in the nose, a repositioned braking chute, and a new ram-air inlet at the base of the tail fin. The revised aircraft were dubbed "Fencer-B" by NATO, but did not merit a new Soviet designation. For more details, including operational history and variants, click here.

The ANEC I and ANEC II were 1920s British single-engine ultralight aircraft designed and built by Air Navigation and Engineering Company Limited at Addlestone Surrey. One was privately constructed in Brisbane, Australia. The ANEC I and II, designed by W.S Shackleton, were amongst the earliest ultralight aircraft; they were very small, wooden, strut braced high-wing monoplanes. The first ANEC I, registered G-EBHR, first flew at Brooklands on 21 August 1923. It was the first aircraft with an inverted engine, a 696 cc Blackburne Tomtit, to fly in the United Kingdom. The ANEC I was designed to the rules of the 1923 Lympne light aircraft trials, principally an engine capacity limit of 750 cc, and the two aircraft completed that August took part. The main prizes were for fuel economy and the second ANEC I G-EBIL, flown by Jimmy James, shared half of the £1,500 prize with an English Electric Wren for flights of 87.5 miles (141 km) on one gallon (4.54 L) of petrol. He later reached an altitude of 14,000 ft (4,267 m) in it. G-EBIL was evaluated by the Air Ministry in 1924, briefly carrying the RAF serial J7506.[3] Afterwards it was modified with a wingspan greatly reduced from 32 ft to 18 ft 4 in (9.75 m to 5.59 m) and re-engined with a 1,000 cc Anzani engine for entry in the 1925 Lympne August Bank Holiday Races, designated the ANEC IA. Only one more ANEC I was constructed. It was built in Australia by George Beohm, who went on to design the Genairco Biplane, and Horrie Miller. E. W. Beckman, the owner of the aircraft, intended to enter it in the Low-Powered Aeroplane Competition held at Richmond in December 1924, but it was not completed until the following year. The first of the two built in the United Kingdom in 1923, G-EBHR, was exported to Australia in the second half of 1924. The ANEC II was an enlarged version of the ANEC I built for the 1924 Lympne light aircraft trials competition. Following the revised competition rules, it was a two-seater and its more powerful 1,100 cc Anzani inverted V twin-cylinder had the greatest capacity allowed. The wing area was increased by 28% to accommodate the extra weight by a 5 ft 2 in (1.57 m) span extension. It was also longer by almost the same amount. Engine problems kept it from flying in the competition and out of the Grosvenor Trophy race that immediately followed. In 1927 a new owner refitted it with a 32 hp (24 kW) Bristol Cherub III flat twin engine, a larger rudder, and a more conventional undercarriage with larger wheels mounted on a cross axle attached to the lower fuselage with a pair of V-struts. In 1931 another new owner fitted a heavier 30 hp (22 kW) ABC Scorpion engine, another flat twin and, to keep the weight down, reworked it as a single seater. It was in this condition when it was acquired by Richard Shuttleworth in about 1937. Variants ANEC I – three built (Specifications below) ANEC IA – ANEC I with reduced wingspan, one modified. ANEC II – two-seat version, one built.

The Lockheed EC-121 Warning Star was an American airborne early warning and control radar surveillance aircraft operational in the 1950s in both the United States Navy (USN) and United States Air Force (USAF). The military version of the Lockheed L-1049 Super Constellation was used to serve as an airborne early warning system to supplement the Distant Early Warning Line, using two large radomes (a vertical dome above and a horizontal one below the fuselage). It replaced the TBM-3W used by the USN. Some EC-121s were also used for signal intelligence gathering. The EC-121 was introduced in 1954 and phased out in 1978, although a single specially modified EW aircraft remained in USN service until 1982. The USN versions when initially procured were designated WV-1 (PO-1W), WV-2, and WV-3. The USAF Warning Stars served during the Vietnam War both as electronic sensor monitors and as a forerunner to the Boeing E-3 Sentry AWACS. USAF aircrews adopted its civil nickname, "Connie" (diminutive of Constellation) as reference, USN aircrews used the nickname "Willie Victor". For details of development, operational history and variants, click here.

The Diamond D-JET is a composite, five-seat, single-engine very light jet developed by Austrian aircraft manufacturer Diamond Aircraft Industries. The intended cost for the aircraft was advertised by the company as being US$1.89 million dollars in March 2009. Development of the D-JET has been disrupted by funding shortfalls during the Great Recession. By February 2013, the development program had been suspended pending company reorganization, which included the workforce related to the D-JET being laid off. During May 2014, Diamond confirmed the continued suspension of the programme, but stated that it had not been cancelled. During December 2016, a majority share of Diamond Aircraft Canada was sold to Chinese firm Wanfeng Aviation; reportedly, this shall result in a detailed re-assessment of the D-JET program, including options for the potential resumption of its development. The Diamond D-JET is a very light jet aircraft, seating up to five personnel and powered by a single engine. A key attribute of the design was its high level of stability during flight, which was reportedly present through its full envelope even during challenging manoeuvres. As a result of its clean exterior design, the D-JET possesses relatively low drag, enabling the aircraft to glide in excess of 65 miles from its 25,000-foot ceiling altitude. The cabin of the D-JET was intended to feature various design elements to enhance onboard comfort, such as the proposed seating layout and the low vibration levels present during flight, for both passengers and crew. The center cockpit pedestal is cantilevered to ease entrance and egress in comparison to some competitors. Separated baggage compartments are located within the interior of the aircraft's nose and to the aft of the main cabin, both of which being externally accessed. The D-JET is powered by a single Williams FJ33-4A turbofan engine, which is equipped with an electronically controlled full-authority digital engine control (FADEC) system. Various functions, such as engine startup and over-speed selection prevention, have been automated and are seamlessly performed by the FADEC system. For redundancy, the dual-channel FADEC system uses four independent electrical power sources in addition to battery backup. Diamond opted to adopt a centerline location for the engine, air for which is fed through inlets embedded into the wing roots. The central location of the engine places makes it close to the center of gravity of the D-JET, reducing pitch forces, however, there are some drawbacks to this approach, including elevated air losses within the ducting arrangement used and a greater likelihood of foreign object ingestion. According to aviation publication Flying Magazine, the controls of D-Jet "feel completely natural...stability is excellent, and I found the workload to be very low". Akin to most jet aircraft, possessing a wide range between minimum and maximum airspeeds, the D-Jet has a larger pitch trim range than a piston-engined counterpart, thus use of the trim control through the takeoff and landing procedures is necessitated to a greater degree than propeller-driven aircraft. The D-Jet is outfitted with relatively large slotted flaps, which were reportedly crucial to achieve the 61-knot maximum stall speed certification required by any single-engine aircraft. These flaps, which resulted in no meaningful pitch changes during retraction or extension, were designed to ease their usage. The avionics of the D-JET comprise a Garmin G1000 glass cockpit, the large multi-function display of which taking center-place on the cockpit dashboard, akin to aircraft such as the Citation Mustang. For de-icing purposes, Diamond opted for pneumatic boots on the wing's leading edges, bleed air for heating the inlets and ducts, and electric heating for the windshields and probes; in particular, Goodrich developed a considerably thinner de-icing system for the D-JET. The landing gear is electrically-actuated on later-built prototypes; atypically, the landing gear is designed to be used as an air brake during landing approaches, being deployable at speeds as high as 200 knots. Maneuvering on the ground was achieved via a nosewheel steering system, actuated via a mechanical linkage to the pedals. According to Diamond, the D-JET could be operated from 3,000-foot runways, assuming that they are both dry and uncontaminated. For details of development, click here.

The Nakajima B6N Tenzan (Japanese: 中島 B6N 天山, "Heavenly Mountain", Allied reporting name: "Jill") was the Imperial Japanese Navy's standard carrier-borne torpedo bomber during the final years of World War II and the successor to the B5N "Kate". Due to its protracted development, a shortage of experienced pilots and the United States Navy's achievement of air superiority by the time of its introduction, the B6N was never able to fully demonstrate its combat potential. The B5N carrier torpedo-bomber's weaknesses had shown themselves early in the Second Sino-Japanese War and, as well as updating that aircraft, the Imperial Japanese Navy began seeking a faster longer-ranged replacement. In December 1939 it issued a specification to Nakajima for a Navy Experimental 14-Shi Carrier Attack Aircraft capable of carrying the same external weapons load as the B5N. The new plane was to carry a crew of three (pilot, navigator/bombardier and radio operator/gunner) and be of low wing, cantilevered, all-metal construction (though control surfaces were fabric-covered). Further requirements included a top speed of 250 knots (460 km/h; 290 mph), a cruising speed of 200 knots (370 km/h; 230 mph) and a range of 1,000 nmi (1,900 km; 1,200 mi) with an 800 kg (1,800 lb) bomb load or 2,072 nmi (3,837 km; 2,384 mi) without external armament. The Navy had requested installation of the proven Mitsubishi Kasei engine as the B6N's powerplant but Engineer Kenichi Matsumara insisted on using Nakajima's new 1,870 hp (1,390 kW) Mamoru 11 14-cylinder air-cooled radial due to its lower fuel consumption and greater adaptability. This became an unfortunate choice as the Mamoru engine was plagued with mechanical defects and never achieved its expected power rating. Constrained by the standard-sized aircraft elevators then in use on most Japanese carriers, designer Matsumara was obliged to use a wing similar in span and area as that of the B5N and to limit the aircraft's overall length to 11 m (36 ft). This latter restriction accounted for the B6N's distinctive swept-forward tail fin and rudder. The outer wing panels folded upward hydraulically, reducing the B6N's overall span from 14.9 m (49 ft) to approximately 6.3 m (21 ft) for minimal carrier stowage. In order to lessen increased wingloading due to the heavier powerplant, Fowler flaps were installed which could be extended beyond the wing's trailing edge. These were normally lowered to an angle of 20 degrees during take-off and 38 degrees when landing. Despite the use of these flaps, however, the B6N had a much higher stall speed than its predecessor. The prototype B6N1 made its maiden flight on 14 March 1941. Following continued testing, however, several problems became evident. In particular, the aircraft exhibited an alarming tendency to roll while in flight, the cause of which was traced to the extreme torque developed by the four-bladed propeller. To compensate, the aircraft's tail fin was thinned down and moved 2 degrees ten minutes to port. This modification greatly improved the plane's handling characteristics. A total of 1268 units were built. For more details of design annd developmennt, and operational history annd variants, click here.

The Mitsubishi A6M "Zero" is a long-range carrier-based fighter aircraft formerly manufactured by Mitsubishi Aircraft Company, a part of Mitsubishi Heavy Industries. It was operated by the Imperial Japanese Navy (IJN) from 1940 to 1945. The A6M was designated as the Mitsubishi Navy Type 0 carrier fighter (零式艦上戦闘機, rei-shiki-kanjō-sentōki), or the Mitsubishi A6M Rei-sen. The A6M was usually referred to by its pilots as the Reisen (零戦, zero fighter), "0" being the last digit of the imperial year 2600 (1940) when it entered service with the Imperial Navy. The official Allied reporting name was "Zeke", although the name "Zero" was used colloquially as well. The Zero is considered to have been the most capable carrier-based fighter in the world when it was introduced early in World War II, combining excellent maneuverability and very long range. The Imperial Japanese Navy Air Service also frequently used it as a land-based fighter. In early combat operations, the Zero gained a reputation as a dogfighter, achieving an outstanding kill ratio of 12 to 1, but by mid-1942 a combination of new tactics and the introduction of better equipment enabled Allied pilots to engage the Zero on generally equal terms. By 1943, the Zero was less effective against newer Allied fighters. The Zero lacked hydraulic boosting for its ailerons and rudder, rendering it difficult to maneuver at high speeds. By 1944, with Allied fighters approaching the A6M levels of maneuverability and consistently exceeding its firepower, armor, and speed, the A6M had largely become outdated as a fighter aircraft. However, as design delays and production difficulties hampered the introduction of newer Japanese aircraft models, the Zero continued to serve in a front-line role until the end of the war in the Pacific. During the final phases, it was also adapted for use in kamikaze operations. Japan produced more Zeros than any other model of combat aircraft during the war. Number built 10,939 For extensive details of design and development, operationnal history and variants, click here.