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Custer Channel Wing aircraft were designed to produce an aircraft that could be flown at a human jogging speed, around 10 kts. The principle involved here is our old mate Bernoulli's - increasing the velocity of a fluid reduces the pressure in the fluid. In this aircraft design, the velocity of the air is created by the rearward acceleration imparted by the pusher propellers located within the semi-circular sections of the wings. The generation of Lift in this manner enables the aircraft to rise from the ground at a very low groundspeed, and vice versa for landing.

The channel wing is an aircraft wing principle developed by Willard Ray Custer in the 1920s. Custer's summary of his invention was that the key to the lift created by a wing is the velocity of the stream of air passing over the wing, not the velocity of the airplane itself: It's the speed of air, not the airspeed!

A wing functions because the air over the wing has a lower pressure than the air under it. The conventional aircraft must reach a significant minimum speed before this pressure differential become large enough that it generates sufficient lift to become airborne. In Custer's channel wing the rotating propeller will direct a stable stream of air backwards through the channel. A propeller will at the low pressure side normally be supplied by air from all directions. Since the half-tube prevents air from being drawn from below, the air will be sucked through the channel instead. This creates a strong low pressure area in the channel, which again generates a lift. The regular design outer wings do generate lift, but are set at a dihedral for roll stability as is common practice in aircraft design.

The concept was shown to work, but although the construction functions very well at relatively low speeds,at higher speeds, at high propeller RPM, oscillations would occur in the areas around the propeller, causing increased noise as well as creating long term destructive vibrations in the structure. The twin layout had a higher risk of loss of control during a single engine failure situation, since the production of lift is dependant on the operation of the propeller.

The Baumann Brigadier was chosen by Willard Ray Custer as the basis of his Custer CCW-5, which used the fuselage and tail of the Brigadier. The Baumann Brigadier was a prototype American light transport aircraft of the late 1940s. It was a twin-engined monoplane, which, unusually, was of pusher configuration. Only two were built, plans for production never coming to fruition.

Here is Custer speaking about his aircraft on The American TV show "I've got a Secret"

The first business jet developed by the firm, it became the first of a family of business jets to be produced under the same name; of these, both the smaller Falcon 10 and the larger trijet Falcon 50 were direct derivatives of the Falcon 20.

Initially known as the Dassault-Breguet Mystère 20, approval to proceed with development of the aircraft was issued during December 1961. It is a low-wing monoplane design, powered by a pair of rear-mounted General Electric CF700 turbofan engines. On 4 May 1963 the prototype made its maiden flight. The first production aircraft was introduced on 3 June 1965. On 10 June 1965, French aviator Jacqueline Auriol achieved the women's world speed record using the first prototype.

The Dassault Falcon 20 is a French business jet, often considered to be an easy to fly and relatively visually appealing aircraft. The favourable flight qualities of the aircraft meant that there was no need to incorporate a stick pusher or stall-barrier systems in order to achieve its predictable stall behaviour. The flight controls of the Falcon 20 are hydraulically-powered, augmenting the mechanical pushrods between the cockpit controls and the flight control surfaces. In the event of complete hydraulic failure, the aircraft can be practically flown without any augmentation. The controls incorporate an artificial feel system, optimising the sensations perceivable to the operating pilot to be smooth, predictable, and precise.

The Falcon 20 is furnished with a highly swept wing; it is equipped with leading-edge slats to improve its slow speed performance and decrease the stalling speed. When approaching a high angle of attack, the slats are automatically deployed; when nearing a potential stall, the inner section of the slats then retract to provide for a stable and predictable stall with effective aileron controls throughout.

Three Falcon 20's served with the RAAF VIP Squadron.

For more details of the development, design operational history and 21 variants, click here.

Specvifications below are for the Falcon 20F model.

The Dassault Falcon 2000 is a business jet produced by French Dassault Aviation, a member of its Falcon business jet line. Developed from the Falcon 900 trijet, the smaller twinjet has less range.

The Falcon 900 fuselage was shortened by 7 ft (2.1 m) to carry up to 10 passengers. The wing leading edge was modified and its inboard slats were removed. It was introduced in 1995 for $17.85 million, while the 2023 Falcon 2000LXS lists for $36 million.

Variants

Falcon 2000
Original version certified in 1994[4] with CFE (General Electric & AlliedSignal) CFE738-1-1B turbofans,[5][6] with 5,918 pounds-force (26.32 kilonewtons) of thrust each, a range of 2,841 nautical miles [nmi] (5,262 km; 3,269 mi) range and Collins Pro Line 4 avionics suite.[2]
Falcon 2000EX
Re-engined variant certified in 2003 with Pratt & Whitney Canada PW308C turbofan engines,[5] 7,000 lbf (31 kN) each, offering a 3,878 nmi (7,182 km; 4,463 mi) range.
Falcon 2000EX EASy
Marketing designation for a 2000EX with changes to pressurisation and oxygen systems, certified in 2004, and Honeywell Primus Epic-based EASy avionics suite, including synthetic vision. Undertook steep approach trials at London City Airport on 18 March 2010, becoming the first Dassault twin-jet to visit apart from the much older, diminutive Dassault Falcon 10.
Falcon 2000DX
Updated model certified in 2007[4] and based on the 2000EX EASy with the same PW308C turbofans. Shorter-range of 3,250 nmi (6,020 km; 3,740 mi) for $28.5 million.
Falcon 2000LX

Longer-range 2000 variant of the Falcon 2000EX EASy, with the addition of Aviation Partners Blended Winglets, giving it a range capability of 4,000 nautical miles (7,400 km; 4,600 mi).[8] The same winglets are certified for the entire Falcon 2000 series as a retrofit kit.
Falcon 2000S
Variant which began testing in 2011 with short field characteristics. Landing distance has been reduced to 705 meters, opening up 50% more airports than other aircraft in this class. Compared to the $5 million more expensive LXS, the S range is shorter by 500 mi (800 km; 430 nmi) by restricting its fuel capacity to 14,600 lb (6,600 kg). It burns 2,350–2,400 lb (1,070–1,090 kg) of fuel in the first hour and 1,600–1,650 lb (730–750 kg) afterwards, and can take off in 4,325 ft (1,318 m) at sea level on a standard day. In 2021, its equipped price was $28.8M. It offers a 3,350 nmi (6,200 km; 3,860 mi) range.
Falcon 2000LXS                (Specifications below)
Replacement for the long-range 2000LX and introduced in 2014. Relative to its predecessor, the Falcon 2000LXS offers greatly improved takeoff and landing performance, superior cabin comfort and reduced emissions. It also has a lower approach speed (194 km/h vs. 210 km/h), enabling it to land in a shorter distance, 689 m vs. 800 m, equivalent to turboprop aircraft. In 2021, its equipped price was $35.1M.
Falcon 2000MRA/MSA
The Maritime Reconnaissance Aircraft (MRA) or Maritime surveillance aircraft (MSA) is a militarized variant based on the Falcon 2000LXS. Six Falcon 2000MSA were ordered by the Japan Coast Guard in 2015, with delivery expected from 2019 onwards.
Falcon 2000 Albatros

Derived from the Falcon 2000MRA, the Falcon 2000 Albatros was selected in 2020 to replace the French Naval Aviation's Falcon 50 Surmar and Falcon 200 Gardian aircraft. The aircraft is designed for maritime surveillance and intervention missions. It will incorporate a multifunction under-fuselage radar, a high-performance electro-optical/infrared (EO/IR) system, observation windows, a Search & Rescue chain release system and dedicated communications systems. Seven units have been ordered and are to be delivered from 2025 onwards, with the acquisition of five additional units planned for a total of twelve aircraft.

The Dassault Falcon 6X is a large, long-range business jet developed by Dassault Aviation in France. Its precursor, the Falcon 5X twinjet, was launched in 2013, rolled-out in 2015 and made its first flight on July 5, 2017, but its development was frozen as its Safran Silvercrest engine failed to meet performance objectives. In December 2017, the Falcon 6X was launched as a stretched version with PW812D turbofans, made its first flight on 10 March 2021, and entered service on 30 November 2023.

It has the widest purpose-built business jet cabin at 2.58 m (102 in). Its 70.7 m2 (761 sq ft) wing allows a 35,135 kg (77,459 lb) maximum weight with 59.9 kN (13,460 lbf) engines, for a 5,500 nmi (10,200 km) range and a Mach 0.90 top speed.

The Falcon 6X is largely based on the Falcon 5X aerodynamics and systems, validated during its preliminary flight test program, but it is optimized to take advantage of its 58–62 kN (13,000–14,000 lbf) PW812D engines for a longer cabin and a greater 5,500 nmi (10,200 km) range, a Mach 0.90 top speed and a Mach 0.85 cruise. Its cabin is 12.3 m (40 ft) long, is 1.98 m (78 in) high by 2.58 m (102 in) wide (the largest in a purpose-built business jet), and can accommodate 16 passengers in three zones with 29 windows, including a galley skylight.

A front-fuselage extension makes its cabin 51 cm (20 in) longer.[30] The Falcon 6X reinforces the 5X new 70.7 m2 (761 sq ft) wing and keeps its digital flight control system and Honeywell Primus Epic EASy III flight deck. The new engine fans have a diameter of 110 cm (44 in), 15 cm (6 in) narrower than the Gulfstreams, with four low-pressure turbine stages instead of five, engine weight is reduced by 91 kg (200 lb). Its empty weight increases by 1,030 kg (2,270 lb) or 5.7%, from 18.1 to 19.2 t (40,000 to 42,300 lb), due to heavier engines, fuel system and structural reinforcements.[31] The Falcon 6X will be the first Dassault aircraft with a nitrogen inerting system.

The Dassault Falcon 7X is the second largest of its Dassault Falcon line. Launched at 2001 Paris Air Show, its first flight was on 5 May 2005 and it entered service on 15 June 2007. The Falcon 8X is derived from the 7X with a longer range of 6,450 nautical miles (11,950 km) afforded by engine optimizing, aerodynamic refinements and an increase in fuel capacity. Featuring an S-duct central engine, it and the Falcon 900 are the only two trijets in production.

It was first presented to the public at the 2005 Paris Air Show. The aircraft has received its type certification from both the Federal Aviation Administration and European Aviation Safety Agency (EASA) on 27 April 2007. The first 7X, MSN05, entered service on 15 June 2007. The hundredth was delivered in November 2010. It conducted high altitude airport tests at 4,400 m (14,500 ft) in Daocheng in 2014.

Three Falcon 7X's are in service with RAAF Squadron 34, the first arriving in 2018 and the others in 2019.

For details of the development, design, operational history and the larger 8X variant, click here.

The Falcon 900 is a development of the Falcon 50, itself a development of the earlier Falcon 20. The Falcon 900 design incorporates composite materials and an S-duct to feed the central engine.

Improved models include the Falcon 900-B, featuring improved engines and increased range, and the Falcon 900EX featuring further improvements in engines and range and an all-glass flight deck. The Falcon 900C is a lower-cost companion to the Falcon 900EX and replaces the Falcon 900B. Later versions are the Falcon 900EX EASy and the Falcon 900DX. At EBACE 2008, Dassault announced another development of the 900 series: the Falcon 900LX, incorporating high mach blended winglets designed by Aviation Partners Inc. The same winglets are certified for the entire Falcon 900 series as a retrofit kit.

The RAAF operated five Falcon 900's in No 34 Squadron from 1989 to 2003.

For details of the 10 variants, click here.

Specifications below are for the 900B variant.

The Dassault M.D.320 Hirondelle was a French 14-seat utility transport aircraft of the 1960s, designed and built by Dassault Aviation, in prototype form only.

In 1967 the French Air Force, investigating replacement aircraft for the Douglas DC-3 and Beechcraft 18 twin-engine aircraft being used for light transport and pilot navigation training, solicited proposals from the French industrial community, specifying that any submittals would be powered by 650 kW (870 hp) Turbomeca Astazou turboprops.

In response to this request, Dassault designed and constructed a single prototype M.D.320, later named Hirondelle (Swallow). Design and construction were fairly rapid, due to extensive use of Dassault Falcon 20 elements such as the fuselage. The fuselage length and volume were identical to the Falcon 20, and its wing and control surfaces were adaptations of the 20.

The Hirondelle was an all-metal low-wing monoplane with swept vertical tail and slightly swept wing and tailplane, supported on a retractable tricycle undercarriage, with the main gear retracting into the engine nacelles.

The Hirondelle had a circular cross-section fuselage with accommodation for a crew of two and room for a maximum of 14 passengers with 5 round windows on each side of the pressurized cabin.

The prototype, (French civil registration F-WPXB), was powered by two Turbomeca Astazou XIVD turboprop engines mounted in wing nacelles, driving three-blade fully feathering propellers. Production aircraft would have been powered by Turbomeca Astazou XVI engines.

The airframe was designed using fail-safe principles and the wings contained integral fuel cells.

The aircraft had some similarities with the two-engine British-built de Havilland Dove but used a trimotor configuration.

Design work on the DHA-3 began in 1946 after DHA identified a need to replace the de Havilland Dragon biplane then in widespread use in Australia. Although the British parent company's Dove was being produced at the same time, DHA saw that the Dove was not entirely suitable for Australian conditions. Using the Dove as a starting point, DHA designed an aircraft with three four-cylinder Gipsy Major engines instead of the Dove's two Gipsy Queen six-cylinder engines and a fixed tailwheel undercarriage instead of the Dove's retractable tricycle undercarriage. Like the Dove the DHA-3 was sized to carry 8 to 9 passengers with a single pilot.

The result was an aircraft with the same wingspan as the Dove and a slightly shorter fuselage. The name 'Drover' was selected by Sir Geoffrey de Havilland after suggestions for a name were invited from DHA employees. The first DHA-3 Mk. 1 Drover took to the air at Bankstown Airport on 23 January 1948 piloted by Brian (Black Jack) Walker, DHA's chief test pilot. The aircraft was subsequently flown by Walker to Melbourne for trials by the Australian Department of Civil Aviation, a flight of 460 miles, achieving 140 mph and a fuel consumption of approximately 22 gallons per-hour. During trials a single-engine rate-of-climb of 240 feet per-minute at sea level was obtained.

The second aircraft did not fly until December 1949, while the first aircraft was delivered in October that year.

For more details of development, operators and variants, click here.

Specificatons below are for the Mk 3 Drover.

Capable of accommodating 6–8 passengers, it proved an economical and durable craft, despite its relatively primitive plywood construction.

Developed during the early 1930s, the Dragon Rapide was essentially a smaller, twin-engined version of the four-engined DH.86 Express, and shared a number of common features, such as its tapered wings, streamlined fairings and Gipsy Six engines. First named the "Dragon Six", the type was marketed as "Dragon Rapide" and later simply known as the "Rapide". Upon its introduction in summer 1934, it proved to be a popular aircraft with airlines and private civil operators alike, attaining considerable foreign sales in addition to its domestic use.

Upon the outbreak of the World War II, many of the civil Rapides were impressed into service with the Royal Air Force (RAF) and Royal Navy. Referred to in military service by the name de Havilland Dominie, the type was employed for radio and navigation training, passenger transport and communications missions. British training aircraft had names with educational associations, and dominie is a Scots term for a school teacher.

For more details of the DH-89, including wartime service and variants, click here.

It was a monoplane successor to the prewar de Havilland Dragon Rapide biplane. The design came about from the Brabazon Committee report which, amongst other aircraft types, called for a British-designed short-haul feeder for airlines.

While standard passenger versions of the Dove would carry between eight and eleven passengers, the cabin was designed to allow operators to convert between higher and lower density seating configurations. Features such as a single aircraft lavatory and an aft luggage compartment could be removed to provide for increased seating capacity. Various specialised models were produced for other roles, such as aerial survey, air ambulance, and flying classroom A strengthened cabin floor structure was used to enable concentrated freight loads to be carried as well. The Dove could also serve as a dedicated executive transport, and in such a configuration it was capable of seating a total of five passengers; the executive model proved to be popular with various overseas customers, particularly those in the United States.

For more details, including the 18 models or modifications, click here.

Specifications below are for the 11 seat Dove 7.

It was a development of the twin-engine de Havilland Dove, with a stretched fuselage and two more engines. It was designed as a rugged, conventional low-wing monoplane with tricycle undercarriage that could be used on regional and commuter routes. A total of 149 were built, and it was also exported to about 30 countries. Herons later formed the basis for various conversions, such as the Riley Turbo Skyliner and the Saunders ST-27 and ST-28.

Immediately after the Second World War, the aircraft manufacturer de Havilland developed the DH.104 Dove, a small twin-engined passenger aircraft intended as a replacement for the earlier Dragon Rapide, which soon proved to be successful. As a further development, the company basically enlarged the Dove; the fuselage was lengthened to make room for more passengers or freight, and the wingspan was increased to make room for two more engines. The Heron was of all-metal construction, and was laid out as a conventional design; the resulting aircraft could use many of the parts originally designed for the Dove, thus simplifying logistics for airlines using both types.

Following the successful completion of the prototype trials as a regional airliner, series production of the Heron began. The first deliveries were to NAC, the New Zealand National Airways Corporation (later part of Air New Zealand).

Basic price for a new Heron in 1960 was around £60,000, minus radio.

For details of development, operational history and variants, click here.

Specifications below are for the Heron 2D.

The de Havilland DH.88 Comet is a British two-seat, twin-engined aircraft built by the de Havilland Aircraft Company. It was developed specifically to participate in the 1934 England-Australia MacRobertson Air Race from the United Kingdom to Australia.

Development of the Comet was seen as both a prestige project and an entry into the use of modern techniques. It was designed around the specific requirements of the race. Despite being made of wood, it was the first British aircraft to incorporate in one airframe all the elements of the modern high speed aircraft - stressed-skin construction, cantilever monoplane flying surfaces, retractable undercarriage, landing flaps, variable-pitch propellers and an enclosed cockpit.

Three Comets were produced for the race, all for private owners at the discounted price of £5,000 per aircraft. The aircraft underwent a rapid development cycle, performing its maiden flight only six weeks prior to the race. Comet G-ACSS Grosvenor House emerged as the winner. Another two Comets were built after the race. The Comet established many aviation records, both during the race and in its aftermath, as well as participating in further races. Several examples were bought and evaluated by national governments, typically as mail planes. Two Comets, G-ACSS and G-ACSP, survived into preservation, while a number of full-scale replicas have also been constructed.

For details of the development and design, operational history of the five units produced, and the records 

achieved, click here.

The de Havilland DH.90 Dragonfly is a 1930s British twin-engined luxury touring biplane built by the de Havilland Aircraft Company at Hatfield Aerodrome.

The Dragonfly shares a clear family resemblance with the Dragon Rapide, but is smaller and has higher aspect ratio, slightly sweptback wings. The lower wing has a shorter span than the upper, unlike the DH.89, and the top of the engine nacelles protrude much less above its surface because the fuel tank had been moved to the lower centre section. Structurally, too they are different: the Dragonfly had a new preformed plywood monocoque shell and strengthened fuselage. It was designed as a luxury touring aircraft for four passengers and a pilot, with provision for dual controls. The first aircraft, G-ADNA, first flew on 12 August 1935. The Dragonfly achieved maximum performance on low power, by using the new construction methods developed for the de Havilland Comet racer, and therefore was expensive to buy (£2,650). In modern terms, it was an executive transport, aimed at wealthy private individuals, often via the companies they owned.

The first delivery was made in May 1936. Some 36 new-build Dragonflies went to private and company owners, about 15 to airlines/air taxis and three to clubs. Two each went to the Danish and Swedish air forces, and the Royal Canadian Mounted Police had four to combat rum-runners. Production ended in 1938.

By 1939, several aircraft had moved from private to commercial use, like the fleet built up by Air Dispatch Ltd at Croydon Airport, headed by The Hon Mrs Victor Bruce. Amongst her seven examples were also some ex-airline machines. They were used as air taxis between the various London airports, and also as Army Cooperation night flying trainers. Western Airways of Weston-super-Mare Airport used its Dragonfly on a scheduled service via Birmingham to Manchester.

Seven airframes were shipped to Canada, and erected by de Havilland Canada, where they served a variety of small commercial operators, the R.C.M.P. and two with the R.C.A.F. At least one, CF-BFF, was fitted with Edo floats, and used commercially.

In about 1937, three Dragonflies were bought by the Romanian government for crew training, appearing on their civil register.

At the start of World War II, about 23 Dragonflies were impressed into the R.A.F and Commonwealth air forces, some six surviving to 1945. Overall, there were about thirteen flying in that year.

Variants

DH.90 : First prototype only. Two 130 hp (97 kW) de Havilland Gipsy Major I
DH.90A : Two 142 hp (106 kW) de Havilland Gipsy Major 1C or D (postwar, essentially identical) or the earlier, very similar Major II in prewar aircraft.
Dragonfly Seaplane: the addition of aluminium floats, strengthened attachment points, an extra cabin door and a wing walkway, increased the empty weight to 3,110 lb (1,410 kg) and lowered the maximum speed to 125 mph (200 km/h)

Australian Operators

• Qantas
• Royal Australian Air Force
• Adastra Aerial Surveys
• Connellan Airways
• Bush Pilots Airways

The D.H.86 was conceptually a four-engined enlargement of the successful de Havilland Dragon, but of more streamlined appearance with tapered wings and extensive use of metal fairings around struts and undercarriage. The most powerful engine made by de Havilland, the new 200 hp (149 kW) Gipsy Six, was selected. For long-range work the aircraft was to carry a single pilot in the streamlined nose, with a wireless operator behind. Maximum seating for ten passengers was provided in the long-range type; however, the short-range Holyman aircraft were fitted with twelve seats.

The prototype D.H.86 first flew on 14 January 1934, but the Qantas representative Lester Brain immediately rejected the single-pilot layout because he anticipated pilot fatigue over long stretches, and the fuselage was promptly redesigned with a dual-pilot nose. Only four examples of the single-pilot D.H.86 were built, and of these the prototype was rebuilt as the dual-pilot prototype. When she entered service in October 1934 the first production aircraft, Holymans' single-pilot D.H.86 Miss Hobart, was the fastest British-built passenger aircraft operating anywhere in the world. Despite de Havilland's predictions to the contrary, the dual pilot type with its lengthened nose proved to be even faster.

Investigations in 1936 following a series of fatal crashes resulted in late production aircraft being built with additional fin area in the shape of vertical "Zulu Shield" extensions to the tail planes to improve lateral stability – these aircraft were designated D.H.86B.

All that remains of the sixty-two D.H.86 aircraft that were built is what looks lke a pile of scrap metal in a corner at the Qantas Founders Museum, Longreach (Qld.).

For moe information on the development and operational history of the DH86, click here.

Currently produced by Viking Air. The aircraft's fixed tricycle undercarriage, STOL capabilities, twin turboprop engines and high rate of climb have made it a successful commuter passenger airliner as well as a cargo and medical evacuation aircraft. In addition, the Twin Otter has been popular with commercial skydiving operations, and is used by the United States Army Parachute Team and the United States Air Force's 98th Flying Training Squadron.

Twin Otters could be delivered directly from the factory with floats, skis, or tricycle landing gear fittings, making them adaptable bush planes for remote and northern areas. Areas including Canada and the United States, (specifically Alaska) had much of the demand. Many Twin Otters still serve in the far north, but they can also be found in Africa, Australia, Asia, Antarctica, and other regions where bush planes are the optimum means of travel. Their versatility and maneuverability have made them popular in areas with difficult flying environments such as Papua New Guinea. In Norway, the Twin Otter paved the way for the network of short-field airports, connecting rural areas with larger towns. The Twin Otter showed outstanding reliability, and remained in service until 2000 on certain routes.

For more details on the design and development of the Twin Otter, click here.

Specifications below are for the 300 series.

It was Diamond's first twin engine design, as well as the first new European twin-engine aircraft in its category to be developed in over 25 years. In 2004, the DA42 became the first diesel-powered fixed-wing aircraft to perform a non-stop crossing of the North Atlantic.

The Diamond DA42 Twin Star is a twin-engined low-wing cantilever monoplane, commonly used as a general aviation aircraft for touring and training purposes. It is equipped with a retractable tricycle landing gear arrangement and uses a T-tail. The DA42 incorporates a combination of advanced features within the company's first twin-engine design. The airframe is composed of composite materials, making extensive use of carbon fiber reinforced polymers throughout its structure; this construction provides the aircraft with a suitable passive safety level to conform with the established European Aviation Safety Agency (EASA) Part 21 rules, as well as relatively efficient aerodynamics and essentially unlimited airframe life.[3] The carbon-fiber main wing spars possesses exceptional crashworthiness.

The DA42 typically accommodates four people in two rows of seating. All of the seats have been designed for crashworthiness and are complete with automotive-style three-point seat belts; while the seats themselves are fixed in position, the position of the rudder-pedals is adjustable. The front pair of seats are accessed via a front-hinged canopy while a top-hinged door located on the left side provides access to the rear seats. The pilots are housed under a sizable canopy which provides generous external visibility, save for the use of a large fixed sunscreen. Additionally, separate baggage compartments, which are accessible via external hatches, are contained within internal space in the aircraft's nose.

For more details of the development, design, deisel engines and operating history, plus the 10 variants, click here.

The prototype, designated as the DA52, first flew on 3 April 2012 after six months of development. In June 2014 it was announced the production aircraft would be designated the DA62.

The aircraft is available in two weight versions. The "European" version has five seats and a maximum takeoff weight (MTOW) of 1,999 kilograms (4,407 lb), the "US" version has seven seats and a MTOW of 2,300 kilograms (5,071 lb). The lower MTOW of the "European" version is to allow operators to avoid higher weight-based air traffic control user charges. The third row of seating and increased MTOW of the "US" version are available as factory options at extra cost. At the 2016 AERO Friedrichshafen, Christian Dries said a special version with an additional baggage belly pod was under consideration for the air charter market.

By April 2019 more than 120 DA62s had been delivered. Aircraft are built in both Austria and Canada.

245 were built in Oberpfaffenhofen, Germany. In 1983, Hindustan Aeronautics (HAL) bought a production licence and manufactured another 125 aircraft in Kanpur, India. In July 2017, 63 aircraft were still in airline service.

The Dornier 228 is a twin-engine general purpose aircraft, capable of transporting up to 19 passengers or various cargoes. It is powered by a pair of Garrett TPE331 turboprop engines. The Do 228 is commonly classified as a Short Takeoff and Landing (STOL)-capable aircraft, being capable of operating from rough runways and in hot climates. This capability has been largely attributed to the type's supercritical wing which generates large amounts of lift at slow speeds. The Do 228 is typically promoted for its versatility, low operational costs, and a high level of reliability – possessing a dispatch reliability of 99%. RUAG Aviation have claimed that no other aircraft in the same class may carry as much cargo or as many passengers over a comparable distance as fast as the Do 228 NG. (New Generation).

The rectangular shape of the Do 228's fuselage section and large side-loading doors make it particularly suitable for utility operators, which is a market that Dornier had targeted with the type from the onset. According to Flight International, one of the more distinguishing features of the Do 228 is the supercritical wing used. The structure of the wing is atypical, consisting of a box formed from four integrally-milled alloy panels. Kevlar is used for the ribs, stringers, trailing edge and fowler flaps, and the wing's leading edge is conventional alloy sheet metal. Benefits of this wing over conventional methodology include a 15% reduction in weight, the elimination of 12,000 rivets, and lowering the per-aircraft manufacturing workload by roughly 340 man hours. Both the fuselage and tail are of a conventional design, but make use of chemical milling in order to save weight.

For more details of the design and development of the 228 and 228NG, click here.

Specifications below are for the 228NG.

The Cold War gave rise to a number of fighter designs on both sides of the Iron Curtain that attempted to overcome the probability of sealed runways being destroyed in First Strike missions. These designs incorporated VTOL technology. While engineers were working on developing fighters, someone came up with the idea to apply the technology to military transport aircraft which could quickly deliver armed troops and equipment to hot spots. German engineers developed the Dornier Do31 for this task, and as the Cold War tensions eased, looked to applying the technology to civilian transport.

For more details about the  Do 31 click here, or watch the video below.

This video tells the story of the D031.

The Dyn'Aéro Twin-R is a twin engine kit-built light aircraft based on the single-engine Dyn'Aéro MCR4S, designed and built in France. Its first flight was in March 2011.

The Dyn'Aéro Twin-R is a twin engine development of the four-seat, single-engine Dyn'Aéro MCR4S, with a 580 mm (1 ft 11 in) greater span and increases in tail surface areas. It was originally intended that it should be built from drawings but changes to French multi-engine aircraft regulations led to plans for kit production.

The Twin-R follows previous MCR series structural practice with much use of carbon fibre, notably in the spars and ribs of the wings and control surfaces, which have pre-formed aluminium skins. The fuselage is a carbon fibre monocoque. The wings have constant chord as on the MCR4S, though the increased span raises the aspect ratio to 10.8, and the Twin-R uses the winglets of the early MCR4S versions (2001-2), with curved (in plan) trailing edges, rather than the later, straight edged ones. The aileron span is increased by 20% and the flaps are electrically operated. Like the MCR4S, the Twin-R has a swept fin, ventral fin and T-tail but the fin is taller and the all flying tailplane of greater span. The rudder area is almost doubled and the surface is double hinged to control yaw when one engine is shut down.

The cabin and rear fuselage of the Twin-R are similar to that of the MCR4S. The cabin has a large, forward hinged, one piece canopy with trapezoidal windows aft. It seats the pilot and three passengers in two side-by-side rows. The twin 74 kW (99 hp) Rotax 912ULS flat four engines are wing mounted. The tricycle undercarriage has wing mounted, faired main legs and wheels.

The Twin-R appeared in public for the first time at the AERO Friedrichshafen 2010 show. It flew for the first time on 3 March 2011 piloted by Christian Briand.

Variants

Twin-R
Kit built.
ELA1
Proposed certificated aircraft.

The Eclipse 500 became the first of a new class of Very Light Jets[4] when it was delivered in late 2006. The aircraft is powered by two lightweight Pratt & Whitney Canada PW610F turbofan engines in aft fuselage-mounted nacelles.

Production of the Eclipse 500 was halted in October 2008 due to lack of funding and the company entered Chapter 11 bankruptcy on 25 November 2008. The company then entered Chapter 7 liquidation on 24 February 2009. After a lengthy Chapter 7 procedure, Eclipse Aerospace was confirmed as the new owner of the assets from former Eclipse Aviation on 20 August 2009 and opened for business on 1 September 2009. In October 2011 Eclipse Aerospace announced a new version of the aircraft, the Eclipse 550, which replaced the 500 in production, with deliveries starting in 2013.

In April 2015 Eclipse Aerospace was merged with Kestrel Aircraft to form One Aviation.

The Eclipse 500 is based on the Williams V-Jet II, which was designed and built by Burt Rutan's Scaled Composites in 1997 for Williams International. It was intended to be used as a testbed and demonstrator for their new FJX-2 turbofan engine. The aircraft and engine debuted at the 1997 Oshkosh Airshow.

The V-Jet II had an all-composite structure with a forward-swept wing, a V-tail, each fin of which was mounted on the nacelle of one of the two engines. The airframe was significantly redesigned as an all-metal structure with a T-tail and straight wings. The main cabin shape is essentially all that was retained from the V-Jet II. It was recognized that for an aluminum structure to be cost effective, new manufacturing techniques would have to be developed. One of the primary processes used was friction stir welding, in which the skin and underlying aluminum structure are welded together rather than riveted, as traditional for aluminum aircraft. Anti-corrosion bonding techniques were also developed.

For further details of the design and development of the EA500, click here.

The design is based on the EMB 110 Bandeirante, using its wing and engine design merged with an all-new fuselage. The EMB 121 first flew on 10 October 1976.

A modified form of the EMB 121, the EMB 121A1 Xingu II, was introduced on 4 September 1981 with a more powerful engine (PT6A-135), increased seating (8 or 9 passengers) and a larger fuel capacity.

Before production ceased in August 1987, Embraer had produced 106 EMB 121 aircraft, 51 of which were exported to countries outside Brazil. Currently, the French Air Force is the largest operator with 23 aircraft still in service.

Variants

EMB 121A Xingu I

Pratt & Whitney Canada PT6A-28

EMB 121A1 Xingu II

Pratt & Whitney Canada PT6A-135

EMB 121B Xingu III

Projected stretched development, not proceeded with,[2] to have been powered by Pratt & Whitney Canada PT6A-42 engines.

EMB 123 Tapajós

planned version with Pratt & Whitney Canada PT6A-45

VU-9

Brazilian Air Force designation

Specifications below are for the EMB 121A1 Xingu II.

The first prototype, with the military designation YC-95, was flown on 26 October 1968. and two other prototypes were built, known as EMB 100. By 1969 an order was placed for 80 production aircraft, by now known as EMB 110 Bandeirante, for the Brazilian Air Force (FAB) with the newly formed aircraft company Embraer. The Bandeirante received its Brazilian airworthiness certificate at the end of 1972, and on 9 February 1973 was made the first delivery to FAB.

Further development of the EMB 110 was halted by the manufacturer in order to shift focus to the larger, faster, and pressurized 30-seat EMB 120 Brasilia.

On Dec 15, 2010, the Brazilian Air Force first flew an upgraded EMB 110 equipped with modern avionics equipment. Designated as the C/P-95, the aircraft has had several new systems installed by Israeli firm Elbit Systems' Brazilian subsidiary, Aeroeletronica. The Brazilian Air Force has an active fleet of 96 EMB-110s.

Over the next 21 years Embraer built 494 aircraft in numerous configurations for a variety of roles. Production was halted in 1990, as the EMB 110 had been superseded by the Embraer EMB 120 Brasilia.

For details of the 31 variants, click here.

Specifications below are for the EMB 110P1A/41 variant.

The Embraer Legacy 450/500 and Praetor 500/600 are a family of mid-size and super mid-size business jets built by Brazilian aircraft manufacturer Embraer. The aircraft family was launched with the Legacy 500 in April 2008 and were the first jets in the size category to feature a flat-floor stand-up cabin and fly-by-wire.

The Legacy 500, with a range of 3,125 nautical miles [nmi] (5,790 km; 3,600 mi) and room for up to 12 passengers, first flew on November 27, 2012, and was certified on August 12, 2014. The shorter Legacy 450 first flew on December 28, 2013, was certified on August 11, 2015, has a range of 2,900 nmi (5,370 km; 3,340 mi), and can accommodate up to 9.

The Praetor 500 and 600 are improvements of the Legacy 450 and 500, respectively, introduced in October 2018 offering more range. The Praetor 600 has a range of 4,018 nmi (7,440 km; 4,620 mi), while the Praetor 500 has a range of 3,340 nmi (6,190 km; 3,840 mi).

Embraer introduced improved variants at the October 2018 NBAA convention, the Praetor 500 and 600, presented on display, with 3,250 nmi (6,020 km; 3,740 mi) and 3,900 nmi (7,200 km; 4,500 mi) of range; the 600 was expected to be certified in the second quarter of 2019 and the 500 in the third quarter of 2019. Both have 22 by 50 in (56 by 127 cm) taller and wider winglets. The $17 million Praetor 500 boosts the fuel capacity of the Legacy 450 from 12,108 to 13,058 lb (5,492 to 5,923 kg) to match the Legacy 500. The $21 million Praetor 600 is based on the Legacy 500 with two tanks on the fuselage belly for 2,928 lb (1,328 kg) more fuel for a 15,986 lb (7,251 kg) capacity, and more powerful 7,528 lbf (33.49 kN) HTF7500E engines.

Praetor 600 flight testing began on 31 March 2018 and 300h were logged with three aircraft by October 2018, while the Praetor 500 flight tests began on 13 September 2018 with 80h accumulated. The synthetic vision system has a flight guidance system for CAT I airports approach with SBAS, allowing decision height to be reduced from 200 to 150 ft (61 to 46 m). Within US SBAS zones, the synthetic vision guidance system (SVGS) allows autopilot-flown instrument approaches down to 150 ft (46 m) height and 1,300 ft (400 m) RVR without the optional Rockwell Collins EVS and HUD.

They are low wing, T-tail airplanes with cabin pressurization, powered by two rear mounted turbofans. The landing gear is fully retractable and designed to be operated on paved runways only. The glass cockpit includes four multi-function displays. The operation is made through a flight management system with autopilot, autothrottle and closed-loop control and monitoring of flight controls Fly-By-Wire. The aircraft are certified for Day, Night, VFR and IFR flights, and are approved for reduced vertical separation minima (RVSM) airspace and flight into known icing conditions, extended flight over water, Category II ILS, operations at high altitude airports up to 13800 ft and steep approach operations.

Embraer offers an enhanced flight vision system constituted by the Rockwell Collins HGS-3500 Head-up display combined with the EVS-3000 Infrared camera, permitting a decision altitude necessitating visual references of 100 ft above touchdown at a projected price of $515,000. Federal Aviation Administration's draft AC 20-167A further proposes a descent below 100 ft if the required visual references can be observed using the EFVS, similar to Cat II and III approaches with limited instrument landing systems in many small airports.

Number built    251

1. Praetor 500 : 42 (as of 26 April 2023)
2. Praetor 600 : 71 (as of 26 April 2023)
3. Legacy 500 : 80 (as of 26 April 2023)
4. Legacy 450 : 58 (as of 26 April 2023)

For operational history and details of variants, , click here. Specifications below are for the Praetor 600.

                                                         Legacy 450

                                                            Legacy 500

                                                            Praetor 500

                                                            Praetor 600