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Joby Aviation is a United States venture-backed aviation company, developing an electric vertical takeoff and landing (eVTOL) aircraft that it intends to operate as an air taxi service. Joby Aviation is headquartered in Santa Cruz, California, and has offices in San Carlos, California; Marina, California; and Munich, Germany. Joby Aviation was founded as Joby Aero on September 11, 2009 as one of several projects incubated by JoeBen Bevirt on his ranch in the Santa Cruz Mountains, using the proceeds from successful exits of previous companies. According to the company's website, the early years were spent exploring different components of electric aviation, including electric motors, flight software, and lithium-ion batteries. This research led Joby to participate in the NASA X-57 Maxwell and LEAPTech projects, before developing its own air taxi concept. Joby's early concept, publicly called the S2, had eight tilting propellers arrayed along the leading edge of its wing and four more tilting propellers mounted on its V-shaped tail. Later, the company moved to a configuration that features six rotating propellers. By 2015, the company was operating subscale prototypes of its eVTOL aircraft, moving to full-scale unmanned prototypes in 2017, and a production prototype in 2019. In 2018, the company announced a Series B funding round of $100 million, led by Toyota AI Ventures. By 2019, the company was in active conversations with the FAA about certifying the aircraft and announced a partnership with Uber's Elevate division. For its first ten years, Joby operated in stealth mode, sometimes leading to skepticism of the company's claims. The first journalist granted access to the aircraft in 2018 agreed not to disclose details about the aircraft. In 2020, however, the company began releasing significantly more information, starting with its January announcement of a $590 million funding round, led by Toyota Motor Corporation. At that announcement, the company revealed its production vehicle. In January 2020, Bevirt was a keynote speaker at the meeting of the Vertical Flight Society. The Joby air taxi is intended to be a four-passenger commercial aircraft with a pilot, capable of traveling up to 150 miles (240 km) on a single charge at a top speed of 200 mph (320 km/h), with a maximum payload of 1,000 pounds. It is designed to take off and land vertically like a helicopter, and transition to horizontal cruise like a fixed-wing aircraft. Nearly silent in flight, the electric-powered aircraft is designed to operate with no emissions and to be 100 times quieter during takeoff and landing than a helicopter. Joby plans to mass-produce its eVTOL, with a plan to operate a piloted on-demand air-taxi service. The aircraft will be operated as a service with per-trip passenger pricing. Joby described the Uber Elevate acquisition as a way to accelerate its commercial launch through Elevate's tools and personnel. Elevate had previously operated a service called Uber Copter, which allowed all Uber users in the New York area to book a trip to John F. Kennedy International Airport, with a car taking riders to a heliport and a helicopter then taking riders to the airport. While the service used Bell 430 helicopters with Uber branding, the aircraft were operated by a separate helicopter company, Heliflite. Joby Aviation cited Elevate's software tools enabling market selection, demand simulation and multi-modal operations as the reasons to purchase Elevate, suggesting the acquisition may play a significant role in Joby's commercial service. Joby has not commented on whether it will continue Elevate's plans to launch in Los Angeles, Dallas, and Melbourne. In Dec 2024 Joby became the first company to fly in Korea’s K-UAM Grand Challenge. For details of development financing, click here. No specifications available.

The Lange Antares is a glider built by Lange Aviation produced with three different wingspans, 18, 20 and 23 meters. The 20 and 23 meter variants can be equipped with a 42-kW electric motor and SAFT VL 41M lithium-ion batteries. The EM 42 is a fixed-shaft brushless DC electric motor running at 190-288 V, and drawing up to 160 A, the 42 kW motor can deliver up to 216 N.m of torque over a speed range of 160-1600 RPM with a total efficiency of 90%. Maximum continuous power is 38.5 kW, the motor weighs 29 kg, and the weight of power electronics is 10 kg. The motor turns a two-blade fixed-pitch propeller, LF-P42, constructed of composite materials, having a diameter of two meters. The battery system consists of two battery packs positioned in the leading edges of both inner wings (72 cells divided into 24 modules containing 3 cells each). The battery life is expected to be 3000 cycles or 20 years. The capacity of the battery is 41 Ah (specific energy 136 Wh/kg and specific peak power 794 W/kg). The batteries can deliver 13 minutes at maximum power and maximum climb speed, and can climb 3,000 meters on one battery charge; in reality, in warm climates, motor and electronics temperature limitations can limit the achievable climb height. The charger is integrated inside the fuselage so when landing elsewhere the pilot merely has to find a (16A) electric outlet socket. The glider has a modem connected to its main computer so that Lange technicians can, in theory, run diagnostics remotely. The same modem allows the pilot remote control & monitoring of the battery charging process. The undercarriage and engine doors are electro-hydraulically operated. The tailwheel is steerable. The wing has an elliptical planform, with winglets and wing-tip wheels. The glide polar shows excellent high speed performance. Variants Antares 18S - 18 meter wingspan pure glider. Antares 18T - 18 meter wingspan glider with Solo 2350 two-stroke gasoline sustainer engine. Antares 20E - 20 meter wingspan with 42 kW electric self-launch capable engine. Antares 23E - 23 meter wingspan with 42 kW electric self-launch capable engine.

The Electric Aircraft Corporation ElectraFlyer-C is an American experimental electric aircraft that was designed by Randall Fishman and produced by his company Electric Aircraft Corporation in 2008. The aircraft is a converted Monnett Moni motor glider intended to test electric propulsion technology for the future Electric Aircraft Corporation ElectraFlyer-X. The design was only intended as a prototype and proof of concept aircraft. The aircraft features a cantilever low-wing, a single-seat enclosed cockpit with a bubble canopy, fixed conventional landing gear and a single 18 hp (13 kW) electric motor in tractor configuration. The sole example built is registered in the US Experimental - Amateur-built category. Constructed from a Monnett Moni motorglider with taildragger landing gear, the original fuselage and wing were retained, but the tail section and tailwheel were extended to improve control on the ground, and to elevate the fuselage. The aircraft is made from sheet aluminum. Its 45.6 ft (13.9 m) span wing has an area of 157 sq ft (14.6 m²). The motor is an 18-horsepower ElectraFlyer direct-drive propulsion kit DC electric motor, powered by a pair of custom-made 5.6 kwh lithium-ion polymer battery packs, weighing 75 pounds (34 kilograms). The batteries are mounted in custom-made, ceramic-stainless steel firewall boxes, sized to fit the space available in the fuselage. The motor returns an 88% efficiency (90% at cruise), with the motor controller consuming 2% of the power. The batteries fitted give an endurance of 1.5 hours and take six hours to recharge at a cost of 70 cents for the power consumed. While descending the propeller generates power to recharge the batteries. The ElectraFlyer-C received its airworthiness certificate on 11 April 2008. Fishman indicated that he would sell the aircraft in April 2009, but as of February 2017 it remains owned by his company.

The Israeli Aircraft Industries Arava (Hebrew: עֲרָבָה, "Willow" or "Steppe" or "Desert", named after the Aravah of the Jordan Rift Valley) is a light STOL utility transport aircraft developed and produced by Israeli aerospace company Israel Aerospace Industries (IAI). It is IAI's first indigenously developed aircraft design to enter production. The Arava had been developed during the 1960s, during which time it was intended to be adopted in large numbers by international customers in both the military and civil markets. Its design draws some influence from the French Nord Noratlas transport plane. Both the Israeli government and IAI's management were enthusiastic to develop the Arava, seeing it as a means of advancing the country's industrial capabilities as well as a source of revenue. On 27 November 1969, the first prototype performed its maiden flight; it would be destroyed on 19 November 1970 after a wing strut failed mid-flight due to excessive flutter. This accident has been attributed as being a major setback to both the Arava's development and its sales opportunities. Despite an otherwise unremarkable development process, the Arava would ultimately only be built in relatively small numbers; many would-be operators, including the Israeli Air Force (IAF), determined that the aircraft lacked appeal over several existing market entrants. By 1973, the Arava programme and IAI were being heavily criticised for overoptimistic forecasting against its actual sales performance. Following an aggressive marketing campaign and new pricing strategies, multiple customers for the type were found, mainly amongst the developing countries, especially in Central and South America, as well as outliers in Swaziland (2018 renamed Eswatini) and Thailand. The IAF was largely unimpressed by the Arava, exercising a short-term lease of three aircraft during the Yom Kippur War of 1973; during the 1980s, the service opted to procure a small fleet of SIGINT-configured Aravas using American aid. In 2004, the IAF retired its Arava fleet. As of 2019, a handful of aircraft remain operational around the world. According to aviation journalist and ex-IAI engineer Danny Shalom, substantial work on the development of what would become the Arava commenced right after the Six-Day War between Israel and several neighbouring nations. Prior to this point, Israel Aerospace Industries (IAI) had largely confined its aircraft manufacturing efforts to producing copies of existing French and American designs, such as the IAI Nesher. However, many of the company's engineers were keen to develop beyond imitation and reverse engineering effort, for IAI and Israel to produce its own unique and indigenously produced aircraft. Around this time, the company foresaw a requirement for a new generation of transport aircraft that would suit operations from runways only 400 meters in length. IAI had forecast the international market demand for such an aircraft to be massive and that, by obtaining only a 20% market share, the company would sell between 400 and 600 aircraft throughout the life of the programme. As the design took shape, key performance objectives included Short-Takeoff and Landing (STOL) capability, the ability to operate the type from unprepared/rough airstrips, as well as the carriage of up to 20 passengers or bulky payloads. The Arava featured a barrel-like fuselage, being relatively short but wide, while the rear of the fuselage was hinged and could swing open for easy and rapid loading and unloading. Its wingspan was long and the twin tails were mounted on booms that ran from the engine nacelles. It was fitted with a fixed nosewheel undercarriage to save weight, while the chosen powerplant was a pair of 715 eshp (533 kW) Pratt & Whitney Canada PT6A-27 turboprop engines. The design configuration bore considerable similarity to the French Nord Noratlas transport plane, which was already being used at that time by the Israeli Air Force (IAF). During June 1968, the Israeli government, headed by Labor leader Levi Eshkol, issued its approval of the initiative, authorising IAI to proceed with full-scale development. The Arava was viewed not only as a sellable product in its own right, but also as a means of enhancing IAI's ability to develop aircraft and thus would heavily influence its work on future projects. Number of units produced: 103 For more details of development and the eleven variants, click here.

The McDonnell Douglas MD-80 is a series of five-abreast single-aisle airliners developed by McDonnell Douglas. It was produced by the developer company until August 1997 and then by Boeing Commercial Airplanes. The MD-80 was the second generation of the DC-9 family, originally designated as the DC-9-80 (DC-9 Series 80) and later stylized as the DC-9 Super 80 (short Super 80). Stretched, enlarged wing and powered by higher bypass Pratt & Whitney JT8D-200 engines, the aircraft program was launched in October 1977. The MD-80 made its first flight on October 18, 1979, and was certified on August 25, 1980. The first airliner was delivered to launch customer Swissair on September 13, 1980, which introduced it into service on October 10, 1980. Keeping the fuselage cross-section, longer variants are stretched by 14 ft (4.3 m) from the DC-9-50 and have a 28% larger wing. The larger variants (MD-81/82/83/88) are 148 ft (45.1 m) long to seat 155 passengers in coach and, with varying weights, can cover up to 2,550 nautical miles [nmi] (4,720 km; 2,930 mi). The later MD-88 has a modern cockpit with Electronic flight instrument system (EFIS) displays. The MD-87 is 17 ft (5.3 m) shorter for 130 passengers in economy and has a range up to 2,900 nmi (5,400 km; 3,300 mi). Specifications below for MD-87. For other models, and details of development, click here. The MD-80 series initially competed with the Boeing 737 Classic and then also with the Airbus A320ceo family. Its successor, introduced in 1995, the MD-90, was a further stretch powered by IAE V2500 high-bypass turbofans, while the shorter MD-95, later known as the Boeing 717, was powered by Rolls-Royce BR715 engines. Production ended in 1999 after 1,191 MD-80s were delivered, of which 116 aircraft remain in service as of August 2022. The MD-80 series is a mid-size, medium-range airliner, featuring a fuselage 14 ft 3 in (4.34 m) longer than the DC-9-50. The small, highly efficient wing design of the baseline aircraft was enlarged by adding sections at the wing root and tip for a 28% larger wing. The aircraft derivative retains the configuration of two rear fuselage-mounted turbofan engines, a T-tail, and has cockpit, avionics and aerodynamic upgrades. The airliner is designed for frequent, short-haul flights for up to 172 passengers depending on airplane version and seating arrangement. The flight deck of the MD-80 aircraft featured advancements from the previous DC-9 series aircraft. Electro-mechanical instrumentation with an attitude-heading reference system was standard, with a multi-panel electronic flight instrument system standard on later build aircraft. Earlier aircraft were upgradeable to EFIS instrumentation. A full flight management system or Performance Management Computer was offered. A traffic alert and collision avoidance system, a state-of-the-art inertial reference system, and LED dot-matrix displays for engine and system monitoring were all available on later build aircraft as standard.

The Short 360 (also SD3-60; also Shorts 360) is a commuter aircraft that was built by UK manufacturer Short Brothers during the 1980s. The Short 360 seats up to 39 passengers and was introduced into service in November 1982. It is a larger version of the Short 330. During the 1970s, the world's commuter airline market began to evolve from the 20-seat class to larger and more comfortable cabins. Short Brothers of Northern Ireland had created the Skyvan in 1962, followed by the related but larger Short 330 in 1974. The Short 360 development was announced in 1980, with the prototype's first flight on 1 June 1981 and type certification awarded on 3 September 1981. The first production Short 360 had its maiden flight on 19 August 1982 and entered service with Suburban Airlines (later merged with Allegheny Airlines/US Airways) in November 1982. After initiating production with the basic model, Short marketed a number of 360 developments. First was the 360 Advanced, in late 1985, with 1,424 shp (1,062 kW) PT6A-65-AR engines. That was followed by the 360/300, in March 1987, with six-blade propellers, more powerful PT6A-67R engines, and aerodynamic improvements, giving a higher cruise speed and improved "hot and high" performance. The 360/300 was also built in 360/300F freighter configuration. Production of the 360 ceased in 1991 after 165 deliveries. The Short 360 is a 36-seat derivative of the 30–33 seat Short 330. In high density configuration, 39 passengers could be carried. The two Short airliners have a high degree of commonality and are very close in overall dimensions. The later 360 is easily identified by a larger, swept tail unit mounted on a revised rear fuselage. The 360 has a 3-foot (91 cm) fuselage "plug" which gave sufficient additional length for two more seat rows (six more passengers), while the extra length smoothed out the aerodynamic profile and reduced drag. Seating is arranged with two seats on the starboard side of the cabin and one seat on the port side. The 360's power is supplied by two Pratt & Whitney PT6A-65Rs. Building on the strengths and reputation of its 330 antecedent, the 360s found a niche in regional airline use worldwide, being able to operate comfortably from 4,500 feet (1,400 m) runways – opening up hundreds of airfields that would otherwise be inaccessible to airliners. With a cruise speed about 215 knots (250 mph; 400 km/h), at an altitude of 10,000 feet (3,000 m), the unpressurized 360 was not the fastest turboprop in its market, but it offered acceptable performance at a reasonable price, combined with ease of service and maintainability. The PT6A turboprops are fully ICAO Stage 3 noise-compliant, making the 360 one of the quietest turboprop aircraft operating today. Variants 360-100 - the first production model with Pratt & Whitney Canada PT6A-65R turboprop engines. 360 Advanced - with PT6A-65AR engines rated at 1,424 shp (1,062 kW) each. The aircraft was later redesignated 360-200. Introduced in late 1985. 360-300 - with more powerful PT6A-67R engines with six-blade propellers. Higher cruise speed and improved performance. 360-300F - the freighter version of the -300,[8] with capacity for five LD3 cargo containers. Short C-23 Sherpa B+ and C variants are military-configured Short 360s operated by the United States military. Twenty-eight C-23B+ were produced by conversions of civilian Short 360 airframes, and the C-23C was a conversion of C-23B and C-23B+.

The Saro A17 Cutty Sark was a British amphibious aircraft from the period between World War I and World War II, built by the British firm Saunders-Roe (also known as SARO). The aircraft was named after the ship Cutty Sark, rather than the garment or the fictional witch. The Cutty Sark was a shoulder-winged four-seat amphibian monoplane with an all-metal hull and plywood covered wings. The above-wing pylon-mounted engines could easily be changed, and a variety of different engines were used to power the type, including 104 hp Cirrus Hermes Mk 1s and 120 hp de Havilland Gipsy IIs. The Saro A19 Cloud was derived from the Cutty Sark. Only 12 Cutty Sarks were built, and none lasted long in service, but the type nevertheless saw service with many users in the United Kingdom, Australia, Canada, New Zealand, China, Japan and the Dominican Republic. In 1928, Sir Alliot Verdon Roe sold Avro. He bought an interest in S. E. Saunders, flying boat manufacturers based at Cowes, Isle of Wight, southern England; the company was renamed Saunders-Roe. The rebranded company’s first new project to reach quantity production was the A17 Cutty Sark. It was a four-seat twin-engined commercial flying boat. While primarily intended for landing and taking off from the water, the Cutty Sark could also make occasional use of land-based facilities, for which purpose the manufacturer could supply an amphibian gear that would attach to various fixing points that were present upon on the structure. In terms of propulsion, the Cutty Sark could be equipped with numerous engine arrangements that would develop a total power output of around 200 hp. Typically, it would be powered by a pair of engines mounted in a tractor configuration within separate nacelles positioned above the wing; this location was readily accessibility while afloat. Seeking to avoid excessive inefficiency and ensure a sufficient safety margin in the event of a forced landing, it was specified that the flying boat’s loading ought not to exceed 106 lb. per hp. The engines could be started from the pilot’s seated position on the flight deck by means of a compressed air-based ignition system, which comprised a compact engine-drive compressor, a reservoir, fuel vaporizers, distributors and remote controls. The lubrication system was entirely contained within the engine, the sump had a capacity of two gallons while a gauge on the side of the crank case displayed the quantity of oil present. Fuel was primarily stored within the wings; the wing tanks supplied fuel to the engines via a pair of gravity tanks, which could contain sufficient fuel for half an hour of flight time, that were located directly behind the engines. The fuel cocks installed upon the gravity tanks could be actuated remotely by the pilot. The gravity tanks were protected by a fireproof baffle. Both the piping and tanks were relatively isolated from most sources of ignition to lower the risk posed by fire, particularly to the hull and the occupants therein; it was for this reason that no fuel pipes were permitted within the hull. Faith in these fire prevention measures were such that smoking was permitted within the cabin. The lubrication system is contained wholly in the engine. A gauge on the side of the crank case shows the quantity of oil in the sump which has a capacity for two gallons. For more details of the construction of the aircraft, and the history of each of the twelve units built, click here. The only single engined version Cutty Sark.

The Saunders-Roe SR.A/1 was a prototype flying boat fighter aircraft designed and built by British seaplane manufacturer Saunders-Roe. It was the first jet-propelled water-based aircraft in the world. The concept behind the SR.A/1 originated during the Second World War as a reaction to Japan's successful use of military floatplanes and the emergence of the turbojet engine. Saunders-Roe presented an initial proposal of their jet-powered seaplane concept, then designated SR.44, to the Air Ministry during mid-1943. In April 1944, the Ministry issued Specification E.6/44 for the type and supported its development with a contract for three prototypes. Development was protracted by Saunders-Roe's work on other projects, the war having ended prior to any of the prototypes being completed. On 16 July 1947, the first prototype made its maiden flight. The SR.A/1 was evaluated by the Royal Air Force (RAF), who concluded that the design was incapable of matching up to the performance of land-based designs. Despite interest from foreign governments, including the United States, no orders for the SR.A/1 materialised. As such, it never entered volume production or saw service with any operators. While interest in the SR.A/1 programme was briefly revived following the start of the Korean War, the aircraft was considered to be obsolete by that point and was again rejected. The SR./A.1 was directly inspired by the modest successes experienced by the Imperial Japanese Navy in using seaplane fighters, such as the Nakajima A6M2-N (an adaptation of the Mitsubishi Zero) and the Kawanishi N1K. Seaplanes had performed successfully during both of the world wars although, according to author H. F. King, their achievements were often not highly publicised or well known. Prior to the introduction of the Gloster Gladiator, every British shipborne fighter was designed with an interchangeable wheel-or-float undercarriage. In theory, seaplanes were ideally suited to conditions in the Pacific theatre of the Second World War, and could turn any relatively calm area of coast into an airbase. Their main disadvantage came from the way in which the bulk of their flotation gear penalised their performance compared to other fighters. Both immediately prior to and during the war, Britain made very little use of seaplane fighters, instead relying upon aircraft carriers and land-based fighters as the basis of their military operations, despite the concept having remained popular with other powers, including Japan, Italy, and France. Proposed seaplane conversions were produced for both the Hawker Hurricane and the Supermarine Spitfire to meet operational needs in the Norwegian Campaign, but were largely curtailed following the rapid German victory in this theatre. No quantity production of seaplane fighters followed. It was in this backdrop that British seaplane manufacturer Saunders-Roe recognised that the newly developed turbojet engine presented an opportunity to overcome the traditional performance drawbacks and design limitations of floatplanes. By not requiring clearance for a propeller, the fuselage could sit lower in the water and use a flying boat-type hull. The prospective aircraft's performance when powered by Halford H.1 engines was projected to be 520 mph at 40,000 ft. Saunders-Roe speculated that, as floatplanes could have staging grounds nearer to their objectives than land-based counterparts, both the time and effort involved in mounting missions, particularly offensive ones, could be reduced. Early jet aircraft were typically restrained in terms of their range due to the high fuel consumption involved, a factor which could be overcome by bringing forward their staging areas, something which a floatplane would be readily capable of doing. Re-basing to virtually any body of water could also be performed with little in the way of setup or ground preparation, according to the company. For more development details, click here.

The McDonnell F3H Demon is a subsonic swept-wing carrier-based jet fighter aircraft designed and produced by the American manufacturer McDonnell Aircraft Corporation. It was the first swept wing jet fighter and the only single-engined carrier-based fighter the company produced. The Demon was developed during the late 1940s and early 1950s to fulfill a United States Navy requirement for a high-performance swept wing naval fighter to succeed the F2H Banshee. On 7 August 1951, the XF3H-1 performed its maiden flight, flown by test pilot Robert Edholm. The original design for a short-range interceptor was reworked into a heavier medium-range all-weather fighter to counter the Mikoyan-Gurevich MiG-15 jet fighter being encountered during the Korean War; however, the addition of about 7,000 lb (3,200 kg) of weight hampered the Demon's performance. The Demon was originally to be powered by the Westinghouse J40 turbojet engine, but the J40 proved unreliable and lacking in thrust, and the program was ultimately abandoned after it became politically controversial in 1955. This necessitated another major redesign of the aircraft to accept the alternative Allison J71 powerplant. On 7 March 1956, the Demon was introduced to operational service. Though the aircraft had insufficient power for supersonic performance and insufficient endurance for its intended general-purpose role, it complemented day fighters such as the Vought F8U Crusader and Grumman F11F Tiger as an all-weather, missile-armed interceptor. The Demon was withdrawn in 1964 and thus did not participate in the Vietnam War. Both it and the Crusader were replaced on Forrestal-class and similar supercarriers by the more capable and versatile McDonnell Douglas F-4 Phantom II, which bears a strong family resemblance, as it was conceived as an advanced development of the Demon. The supersonic F-101 Voodoo of the United States Air Force was similar in layout, but was derived from the earlier XF-88 Voodoo, which also influenced the Demon's layout. Although the existence of the Soviet Union's Mikoyan-Gurevich MiG-15 jet fighter program was unknown to U.S. intelligence at the time, the United States Navy anticipated the appearance of high-performance Soviet jet fighters, and issued requirements for a high-performance swept wing naval fighter on 21 May 1948. McDonnell was one of six aircraft companies that opted to produce a response, beginning development work during 1949. The design team chose to develop an all-new aircraft incorporating a swept wing configuration from the onset rather than adapting a straight wing into a swept wing design as had been done with the competing Grumman F9F Cougar. Roll control was achieved via ailerons augmented by a compact spoiler. Furthermore, both the horizontal and vertical tail surfaces were also swept back.[10] It was the company's first swept wing design, and was amongst the first American aircraft to be primarily armed with missiles rather than cannons. The resulting aircraft, which later received the name Demon, emerged as an all-new design. In order to fulfil the U.S. Navy's requirements, McDonnell agreed to power the aircraft with the Westinghouse J40 engine which was then under development. At the time, the J40 was being promoted by Navy officials for its next generation of aircraft, and was to have thrust of over 11,000 lbf (49 kN)—three times that of the engines used on the McDonnell F2H Banshee. Having gained the interest of U.S. Navy officials, McDonnell was issued with a development contract to produce two XF3H-1 prototypes on 30 September 1949, albeit as a fallback measure to the unconventional Douglas F4D Skyray. At this stage of development, it was envisioned as a day fighter. McDonnell named the aircraft Demon shortly thereafter. The unexpected combat debut of the MiG-15 during the Korean War motivated the U.S. Navy to place the Demon as a top priority, having observed the MiG to have considerably outclassed both the Panther and Banshee; the only American fighter then in service that could equal the MiG was the North American F-86 Sabre, which was only operated by the United States Air Force.[6] Seeking to better respond to the MiG, the U.S. Navy pushed for the aircraft to be heavily redesigned, reorienting it from the short-range interceptor mission once envisioned towards a medium-range all-weather fighter; adapting the design necessitated the addition of 7,000 Ibs. of weight to an aircraft that originally weight 22,000 lbs, thus negatively impacting its performance. Number built: 519 Retired: 1964 For more details of the development, and 8 variants,click here.

The Arsenal VB 10 was a French fighter-interceptor aircraft developed during and shortly after World War II. It was a low-wing monoplane with retractable tailwheel undercarriage and of largely orthodox configuration. The ultimate product of a design that began with the Arsenal VG 10 prior to the war, the VB 10 added a second engine behind the cockpit which drove a second propeller, coaxial with and contra-rotating to the propeller driven by the engine in the nose. In January 1937 Arsenal were given a contract to develop a twin-engined heavy interceptor built from wood, powered by two 590 hp Hispano-Suiza 12X engines mounted in tandem inside the fuselage, driving co-axial propellers in the nose. Work on the VG 10 was abandoned in June 1937 in favour of the VG 20, which was essentially similar but powered by two 900 hp Hispano-Suiza 12Y engines. The VG 20 was abandoned in turn in January 1938, but the design work and studies were used for the design of the all-metal VB 10. For research in the development of the VG 10 and VG 20, Arsenal designed and built the VG 30 powered by a single 690 hp Hispano-Suiza 12X engine, which in turn led to the high-performance fighter prototypes of the VG 30 series. Although the aircraft was first designed, and ordered, in 1940, little progress was made during France's occupation, and the prototype did not fly until after VE day. By then, it was already apparent that the future of the fighter lay with jet power, but development of the VB 10 continued as a safety net for France's nascent jet fighter programmes. In December 1945, a contract for 200 machines was placed by the French government, the first of which flew on 3 November 1947. By the time the fourth had been delivered in September 1948, the entire order was cancelled, with the French Air Force relying on surplus British and American fighters to tide it over until domestically produced jet fighters appeared shortly thereafter.

The Piasecki HUP Retriever or H-25 Army Mule, later UH-25, is a compact single radial engine, twin overlapping tandem rotor utility helicopter developed by the Piasecki Helicopter Corporation of Morton, Pennsylvania. Designed to a United States Navy specification, the helicopter was produced from 1949 to 1954, and was also used by the United States Army and foreign navies. The HUP/H-25 was the first helicopter to be produced with an autopilot and also the first to perform a loop. The design was a product of a competition by the U.S. Navy in 1945 for a compact utility/rescue helicopter to operate from ships including aircraft carriers, battleships, and cruisers. Either 2 or 3 prototypes—designated PV-14 by the factory and XHJP-1 by the Navy—were built and subjected to a side-by-side flight evaluation against the 3 prototypes of the Sikorsky XHJS-1; however, the XHJS was fundamentally a scaled-up version of the Sikorsky H-5, and the increased weight and size magnified the design's problems with maintaining proper weight and balance under varying loading conditions. The Piasecki won the competition, and with the introduction of the aircraft configuration letter "U" for Utility in the 1950s, the aircraft was ordered for production as the HUP-1. The design featured two three-bladed, 35-foot-diameter (11 m) rotors in tandem in which blades could be folded for storage; the relatively small rotor diameter allowed the aircraft to use aircraft carrier elevators with its blades fully extended. The tandem overlapping rotor configuration was a development by Piasecki and was used in future helicopter designs by the company and successors including the H-21, HRB-1/CH-46, and CH-47. The original HUP-1 was powered by a single Continental R-975-34 radial engine, with a take-off rating of 525 hp (391 kW), while later versions used the uprated R-975-42 or R-975-46A with 550 hp (410 kW). To aid search and rescue (SAR) operations, the aircraft was equipped with an overhead winch capable of lifting 400 lb (181 kg), which could lower a rescue sling through an electrically-operated door available after the copilot's seat was folded forward. During a flight demonstration of its capability to withstand high g-force, the type became the first helicopter to perform a loop, albeit unintentionally. For operational history and details of the 9 variabts, click here.

The Piasecki H-21 Workhorse/Shawnee is an American helicopter, the fourth of a line of tandem rotor helicopters designed and built by Piasecki Helicopter (later Boeing Vertol). Commonly called "the flying banana", it was a multi-mission helicopter, capable of being fitted with wheels, skis or floats. The H-21 was originally developed by Piasecki as an Arctic rescue helicopter. The H-21 had cold-weather features permitting operation at temperatures as low as −65 °F (−54 °C) and could be routinely maintained in severe cold weather environments. Piasecki Helicopter designed and successfully sold to the United States Navy a series of tandem rotor helicopters, starting with the HRP-1 of 1944. The HRP-1 was nicknamed the "flying banana" because of the upward angle of the aft fuselage, which ensured that the large rotors could not strike the fuselage in any flight attitude. The name was later applied to other Piasecki helicopters of similar design, including the H-21. In 1949, Piasecki proposed the YH-21 Workhorse, which was an improved, all-metal derivative of the HRP-1, to the United States Air Force (USAF). Using two tandem, fully articulated three-bladed counter-rotating rotors, the H-21 was powered by one nine-cylinder Curtis-Wright R-1820-103 Cyclone supercharged 1,150 hp (858 kW) air-cooled radial engine. After the first flight of the YH-21 on 11 April 1952, the USAF ordered 32 H-21A SAR models and 163 of the more powerful H-21B assault transport variant.[2] The H-21B was equipped with an uprated version of the Wright 103 engine, developing 1,425 shaft horsepower (1,063 kW) and featured rotor blades extended by 6 inches (152 mm). With its improved capabilities, the H-21B could carry 22 fully equipped infantrymen or 12 stretchers, plus space for two medical attendants, as a medevac helicopter. With its Arctic winter capabilities, the H-21A and H-21B were put into service by the USAF and the Royal Canadian Air Force (RCAF) to maintain and service Distant Early Warning Line (DEW) radar installations stretching from the Aleutian Islands and Alaska across the Canadian Arctic to Greenland and Iceland. In 1952, some H-21As were evaluated by USMC helicopter squadron HMX-1 for air assault.[3] In 1957, an H-21B was loaned to the United States Marine Corps (USMC) to evaluate the helicopter as an airborne tug to tow disabled landing ships and amphibious landing vehicles to the beach. During the evaluation, the H-21B towed an LST at 5 kn (9.3 km/h; 5.8 mph) and a simulated tracked amphibious vehicle from the water to the beach.[4] The uprated 1425 hp Wright engine used in the H-21B was also used in subsequent variants sold to both the U.S. Army (as the H-21C Shawnee) and the military forces of several other nations. In 1962, the H-21 was renamed the CH-21 in U.S. Army service. In 1959 Vertol Aircraft, the new name for Piasecki Helicopters, came up with a concept for heavy lift over short distances where between two and six H-21Bs would be linked by beams to lift heavy loads. It was considered to be unsafe, because if one helicopter had mechanical problems during the lift it could unbalance the structure and cause all helicopters to crash. For operational history and details of the 18 variants, click here.

The Camair Twin Navion was a civil utility aircraft produced in the United States in the 1950s by converting single-engine Ryan Navions to twin-engine power. It had been one of two programs to improve the performance of the otherwise-pleasing Navion that was generally considered to be underpowered. The other program had resulted in the TEMCO-Riley D-16A Twin Navion. The Twin Navion design had been undertaken by the White brothers of White Engineering in San Antonio, Texas. They replaced the Navion's engine with a baggage compartment, mounted two engines within new nacelles attached to the wing leading edges, fitted the aircraft with a new tail fin made of fiberglass, and added tip tanks made from recycled WWII napalm canisters. Designated the WE-1, the prototype and the rights were sold to Camair soon after its first flight in 1953 and Civil Aviation Authority type certification was achieved in May 1955 under the name Camair 480. Sales were slow and Camair built only 25 examples before selling off the rights in 1959. The ownership of these rights would change hands twice again over the following decade but only another eight aircraft would be built after the end of Camair's involvement.

The Pilatus PC-8D Twin Porter was a Swiss ten-seat light transport built by Pilatus Aircraft. The type did not go into production and only one was built. Work on the Twin Porter started in 1966, it was a modified Pilatus PC-6 high-wing monoplane with the nose-mounted engine removed and two 290 hp Lycoming IO-540-GIB engines mounted on the wing leading edges.The prototype first flew on 28 November 1967. Only one aircraft was built as flight testing was halted in 1969.

The OMA SUD Redbird is an Italian two-seat, composite light-sport aircraft (LSA) from composite maker OMA Sud. Introduced at the AERO Friedrichshafen show in 2012, the aircraft is supplied complete and ready-to-fly. The Redbird is a carbon fiber, low-wing aircraft with side-by-side configuration seating and fixed tricycle landing gear powered by a 100 hp (75 kW) Rotax 912ULS or Rotax 912iS aircraft engine or a Fiat automotive diesel engine. The cockpit width is 135 cm (53 in).[2][3] The airframe was designed to accommodate retractable gear and the intention is that the European version will offer fixed or retractable gear, while the US LSA version will have fixed landing gear. The aircraft first flew in early 2012, but by 2015 manufacturing arrangements had not been finalized and production not commenced. Reviewer Marino Boric described the design in a 2015 review as, "elegant and usually roomy" and added that it "belongs to the high end UL/LSA segment".

The MAI-223 Kityonok (Russian: МАИ-223 «Китенок», English: MAI-223 Whale Calf) is a single-engine STOL ultralight aircraft developed by the Moscow Aviation Institute's special design bureau (OSKBEC) from 2002. The first production aircraft was delivered in 2008. A crop spraying version is under development. The aircraft is supplied as a kit for amateur construction or complete and ready-to-fly. The Kityonok is a parasol winged, conventionally laid-out ultralight which seats two side by side. The parasol configuration was used to increase wing lifting area to improve STOL performance. Though the prototype had a partly fabric-covered fuselage, later Kityonoks have glass fibre skins everywhere except for control surfaces. The fuselage has an aluminium frame, and the wings have aluminium alloy ribs. The constant-chord wings are swept forward at about 4°, with 3° of dihedral and mount electrically operated flaps. The wings are braced with a V-form pair of lift struts on each side, fixed to the lower fuselage close to the engine mounting and assisted by jury struts. The centre section loads are carried by a centre-line pair of faired cabane struts. The wings can be folded for storage. The tailplane is trapezoidal and set at the top of the fuselage; there is an electrically operated trim tab on the port elevator. The rudder has a ground-adjustable tab. The Kityonok is normally powered by a 73.5 kW (98.6 hp) Rotax 912 ULS flat-four engine driving a three-bladed propeller, though the lower-powered Rotax 503UL or 582 UL are options. Access to the cabin is via two deep, glazed doors. The Kityonok has a conventional undercarriage with main wheels on backward-leaning cantilever legs mounted on torsion bars in the lower fuselage. The mainwheels have hydraulic brakes, and the tailwheel casters. Alternatively it can be equipped with skis or floats. Two production batches of 10 were begun in 2006, on by MAI and one by PRAD. Plans were announced that year for production of the MAI-223SKh crop sprayer version at UZGA (The Ural Works of Civil Aviation) at Ekaterinburg. 4 Kityonoks had been completed by 2009. Though it was intended to produce kits for home building as well as ready-to-fly aircraft, it is not known if any have been made. The third prototype/first production aircraft was delivered to the Tomsk Aero Club in 2008. Variants MAI-223 Base version MAI-223SKh Crop sprayer, announced 2006, first flight 31 August 2007. Can carry up to 160 L (42.2 US gal; 35.2 Imp gal) of chemicals distributed via an 8.56 m (28 ft 1 in) spray bar extending beyond the wings. MAI-208 Autogyro based on MAI-223 fuselage.

The Niki Lightning is a fully enclosed two-seater tricycle autogyro of composite construction, designed and built by Niki Rotor Aviation in Bulgaria. It was introduced in 2009. The Lightning's cockpit pod accommodates a pilot and passenger in tandem. The main rotor is two-bladed, with a pre-rotator. Unconventionally the tail boom is mounted though the centre of the propeller shaft. The boom may be unbolted and removed to aid access to the engine and prop. There is a choice of two very compact D-Motor engines (both liquid-cooled horizontally-opposed side-valve four-strokes): either the 95 hp (71 kW) 4-cylinder LF26 or the 130 hp (97 kW) 6-cylinder LF39. The engine is sited behind the cockpit, driving a 3- or 4-bladed ground-adjustable pusher propeller which is coaxial with the tail boom. The D-Motor engines are direct-drive units redlined at 3,000 rpm. The engines are sited beneath the thrust line of the propeller; instead of using a gearbox, the Lightning uses a multi-belt-drive reduction system of about 3:2 ratio, resulting in an efficient propeller speed of up to 2,000 rpm. This arrangement avoids the necessity of a tailboom beneath the propeller, giving a smoother empenage and reducing drag. Beneath the tail-fin a spring-steel tailskid is fitted, to inhibit propeller strikes. Consuming some 15 L (4.0 US gal; 3.3 imp gal) of avgas per hour, the autogyro has an endurance of 4 hours, with 30 minutes reserve. Its cruise speed of 81 kn (150 km/h; 93 mph) gives the autogyro a range of over 320 nmi (590 km; 370 mi). It has a take-off roll of 70 m (230 ft), and a landing roll of 20 m (66 ft). The Lightning may be flown with its side doors removed. An alternative engine for the Niki Lightning is the Rotax 914UL (but the normal Rotax gearbox would be dispensed with in favour of the drive belts).

The I-11 was a two-seat civil utility aircraft manufactured in Spain in the 1950s. Originally designed by the Spanish aircraft company Iberavia, its first (of two) prototype flew on 16 July 1951. It was a low-wing monoplane of conventional configuration with fixed, tricycle undercarriage and a large, bubble canopy over the two side-by-side seats. Flight characteristics were found to be pleasing, but before plans could be made for mass production, Iberavia was acquired by AISA. The new management decided to continue with development, but made a few changes to the design, reducing the size of the canopy, and replacing the undercarriage with a taildragger arrangement. This configuration entered production in 1952 with an order from the Director General for Civil Aviation for 70 aircraft for use in Spain's aeroclubs. The Spanish Air Force then ordered 125 for use in training and liaison roles. The Air Force then requested 200 aircraft built with the seats in tandem, which were designated I-115 by the manufacturers powered by a 112 kW (150 hp) ENMA Tigre inverted air-cooled engine.Number built 208 Variant I-11 2 prototypes by Iberavia, tricycle undercarriage I-11B Production examples by AISA AISA I-115 Tandem-seat version.

The NAC Fieldmaster was a British agricultural aircraft of the 1980s. A turboprop powered single-engined monoplane, it was built in small numbers and used both as a cropsprayer and a firefighting aircraft. NDN Aircraft was set up in 1976 by Desmond Norman to build the Firecracker trainer. Norman had been a founder of the Britten-Norman company, the manufacturers of the Islander. NDN Aircraft designed a new agricultural aircraft, the NDN-6 Fieldmaster. This was a large single-engined low-winged monoplane with a fixed tricycle undercarriage, powered by a Pratt & Whitney Canada PT6 turboprop engine, the first western-built agricultural aircraft to be designed for turboprop power. Novel features included an integral hopper made of Titanium to carry its chemical payload, which was dispersed via spray nozzles built into the flaps under the aircraft's wings. The first prototype flew on 17 December 1981 at NDN's airfield at Sandown, Isle of Wight. TNDN moved the premises to Cardiff, Wales in 1985, renaming itself the Norman Aeroplane Company (NAC). Production finally started in 1987. It was intended that parts would be produced by UTVA in Pančevo, Yugoslavia (now in Serbia) to be assembled in Cardiff. NAC went into receivership in 1988, after the production of six Fieldmasters, including the prototype.[5] Brooklands Aerospace attempted to continue production, rebuilding one of the Fieldmasters with a more powerful engine as a specialised firefighting aircraft as the Firemaster 65, but these attempts were stopped by the outbreak of civil war in Yugoslavia. Total number built: 10 A final attempt at production was made by the Turkish Aeronautical Association (Türk Hava Kurumu – THK) who started licensed production in 1997. This ended in 1999 after completion of two complete aircraft and a further two airframes lacking engines. Variants NDN-6 Fieldmaster The initial designation for the prototype; one built. NAC Fieldmaster Designation of production aircraft after the formation of the Norman Aeroplane Company (NAC); five built. Brooklands Aerospace Firemaster 65 A rebuilt Fieldmaster with more powerful engine and firefighting equipment; one conversion. THK-TAYSU Production in Turkey by Türk Hava Kurumu (THK); four built

The North American FJ-1 Fury is an early turbojet-powered carrier-capable fighter aircraft used by the United States Navy (USN). Developed by North American Aviation (NAA) starting in 1945, it became the first jet aircraft in USN service to serve at sea under operational conditions. This first version of the FJ was a straight-winged jet, briefly operational during the transition to more successful designs. An evolution of the FJ-1 would become the land-based XP-86 prototype of the United States Air Force's enormously influential F-86 Sabre, which in turn formed the basis for the Navy's carrier-based, swept-winged North American FJ-2/-3 Fury. In late 1944, the USN sought proposals for a follow-on aircraft to supplement its first jet fighter, the McDonnell XFD-1 Phantom; three competing proposals from NAA, McDonnell Aircraft Corporation and Vought were selected. The NAA NA-134 was ordered on 1 January 1945 as the XFJ-1 and would be developed in parallel with the Vought F6U Pirate (the competing McDonnell proposal would eventually evolve into the McDonnell F2H Banshee). The XFJ-1 was a straight-wing, tricycle gear fighter with a single General Electric J35 turbojet fed by an intake passing through the fuselage; to avoid bifurcating the intake and thus increasing drag, the cockpit was placed entirely above the intake duct, giving the aircraft a squat appearance. It was armed with six .50 BMG machine guns mounted next to the air intake, making it the last aircraft ordered by the USN to use .50 BMG guns as its primary armament. The wing, empennage, and canopy strongly resembled that of the piston-engined P-51D Mustang, North American Aviation's highly successful World War II fighter, enclosing a relocated cockpit accommodation further forward in relation to the Mustang's design, to ensure good forward pilot visibility for carrier operations. The first flight of the prototype XFJ-1 was conducted on 27 November 1946, and the first of 30 deliveries of the improved NA-141, designated FJ-1, took place in March 1948.[6] Flown by Navy squadron VF-5A, the FJ-1 made the USN's first operational aircraft carrier landing with a jet fighter at sea on 10 March 1948 aboard USS Boxer, pioneering US jet-powered carrier operations and underscoring the need for catapult-equipped carriers.The Fury was capable of launching without catapult assistance, but on a crowded flight deck the capability was of limited use. Taking off without a catapult launch limited the FJ-1 to a perilous, slow climb that was considered too risky for normal operations. As German research into swept wing aerodynamics was not yet available when the design was finalized, the FJ-1 used a straight wing. Folding wings were not used because dive brakes mounted in the wings made them unfeasible. To conserve carrier deck space, a "kneeling" nose gear strut along with a swiveling "jockey wheel" allowed the FJ-1 to be stacked tail-high, close to another FJ-1. Before the first production FJ-1 was even delivered, the initial order for 100 units was trimmed to only 30 because more promising naval fighter designs had entered development. The production aircraft were initially used in testing at NAS North Island, California. VF-5A, soon redesignated as VF-51, operated the type from Boxer in March 1948 and from USS Princeton in August 1948, but operations did not go well, and the aircraft proved to have weak landing gear. One of the four FJ-1s to operate from Princeton was destroyed in a hard landing on arrival and went over the side; fortunately the pilot was rescued, but further accidents resulted in the cancellation of the operations after only two days. Although VF-51 went to sea on Boxer one more time in May 1949, the FJ-1s were phased out afterwards in favor of the new F9F-2 Panther. Ending its service career in U.S. Naval Reserve units, the FJ-1 was eventually retired in 1953. The one highlight in its short service life was VF-51's win in the Bendix Trophy Race for jets in September 1948. The unit entered seven FJ-1s, flying from Long Beach, California to Cleveland, Ohio, with VF-51 aircraft taking the first four places, ahead of two California Air National Guard Lockheed F-80 Shooting Stars. Number built: 33 (including 3 prototypes) Variants XFJ-1 Prototype aircraft, powered by a 3,820 lbf (17 kN) General Electric J35-GE-2 turbojet engine, three built. FJ-1 Fury Single-seat fighter aircraft, powered by a 4,000 lbf (17.8 kN) Allison J35-A-2 turbojet engine, armed with six 0.50 in (12.7 mm) machine guns, 30 built a further 70 were cancelled.