The Meyers 200 is a single-engined light aircraft produced in the United States in the 1950s and 1960s.

It was the brainchild of Al Meyers and was a development of his Meyers MAC-145 design. The holder of a number of speed records in its class, the Meyers 200 is widely admired for its clean lines, and is also known for its exceptionally sturdy airframe. This strength is derived from a tubular 4130 chrome-moly steel truss structure with aluminum skin that protects occupants.

In 1966, the Aero Commander division of North American Rockwell purchased the rights to the Meyers 145 and 200, as part of a strategy to capture a share of the light aircraft market in the United States. During this time it was in the James Bond film You Only Live Twice. Known briefly as the Aero Commander 200, it soon emerged that the firm could not produce the design economically. Meyers' firm had been virtually hand-building each aircraft and no jigs or tooling for the kind of mass production envisaged by Aero Commander even existed at the time the rights were bought. Having spent US$4 million to produce just US$3 million worth of product, Aero Commander ceased production in 1968 and sold the rights to the Interceptor Corporation, which developed a turboprop-powered version as the Interceptor 400. Ownership of the rights eventually passed to Prop-Jets, Inc., later known as Interceptor Aircraft Corporation. In 2014 the Global Parts Group, via a separately formed affiliate company called Interceptor Aviation Inc, purchased the rights along with all associated assets and intellectual property related to the Meyers 200 and Interceptor 400 model aircraft.

The Meyers 200D has never had an in-flight structural failure and has never had an FAA mandated Airworthiness Directive (AD) issued against the airframe. The 4130 chrome-moly steel tubular roll cage and understructure act like a race car protective cage during a crash. Several Meyers aircraft have been forced down in the trees and off airport runways with documented instances of the occupants walking away with only minor injuries or a broken bone.

For details of the variants, click here.

The Meyers MAC-125 is a light sport aircraft developed in the United States in 1947, produced in a small series as the MAC-145.

The basic design, common to both models, was that of a low-wing cantilever monoplane of all-metal construction with side-by-side seating for two in a fully enclosed cabin. The main gear wheels of the undercarriage were retractable, and the tailwheel was steerable. The aircraft structure incorporated a framework built up of welded steel tube which extended lengthwise from the engine firewall to the rear of the cabin, and spanwise from one undercarriage well to the other. Around this framework was a conventional, monocoque fuselage. The MAC-125 was powered by a single 125-hp engine while the MAC-145 production model had a 145-hp engine instead and a larger tail fin.

The first prototype was lost during spin testing for certification while being flown by Al Meyers. Meyers parachuted to safety, sustaining a broken ankle, and although the aircraft was destroyed, its steel inner structure was salvaged and used to build the second prototype. Certification was subsequently successfully achieved with this aircraft.

Only twenty MAC-145s were built, each to a specific customer order, a business strategy that insulated the Meyers company from the poor market conditions that bankrupted many small American aircraft manufacturers in the late 1940s.

The Meyers OTW (Out To Win) was a 1930s United States training biplane designed by Allen Meyers and built by his Meyers Aircraft Company from 1936 to 1944.

In anticipation for a demand for training aircraft caused by the introduction of a civilian war training scheme (in which civil flying schools would provide primary training for the military), Allen Meyers designed the OTW and formed the Meyers Aircraft Company to build it. The OTW was a conventional biplane with tandem seating for two in open cockpits and a fixed tailwheel landing gear. The prototype was powered by a 125 hp (93 kW) Warner Scarab engine and it first flew on 10 May 1936. The aircraft was produced in two main variants; the OTW-145 powered by a 145 hp (108 kW) Warner Super Scarab, and the OTW-160 powered by a 160 hp (119 kW) Kinner R-5 engine.

A total of 102 were built.

Variants

OTW-125
Production variant with 125hp (93kW) Warner Scarab engine.
OTW-145
Production variant with 145hp (108kW) Warner Super Scarab engine.
OTW-160   (Specifications below)
Final production variant with 160hp (119kW) Kinner R-5 engine.
OTW-KR
One aircraft was re-engined with a 120hp (89kW) Ken-Royce 7G engine.

The Miles M.2 Hawk was a twin-seat light monoplane designed and produced by the British aircraft manufacturer Miles Aircraft Limited during the 1930s. It is the first of the company's aircraft to attain quantity production.

The Hawk's development started in 1932 following a conversation between designer F.G. Miles and Charles Powys, the latter offering Miles hangar space at Woodley Aerodrome to build his proposed affordable twin-seat monoplane. The aircraft was designed by Miles and his wife, while construction of the prototype was mostly performed by the carpenter Harry Hull. On 29 March 1933, the prototype performed its maiden flight.

The aircraft quickly proving its performance to be roughly 50 percent greater than biplane contemporaries. Within 15 months, 47 Hawks had been sold to various domestic customers. An advanced derivative, the Miles Hawk Major, was also quickly developed, alongside several specialised versions of the original aircraft. Amongst other uses, the Hawk was entered into numerous air races. Production of the original Hawk series came to an end during July 1934.

The Miles Hawk was a two-seat lightweight cantilever monoplane. Somewhat unusually for the era, it featured wings that were designed to be folded. The aircraft had an open cockpit with a tandem seating arrangement for two. The airframe was largely composed of spruce, with the exterior being covered by a combination of birch and ply; even elements such as the engine mounts were made of wood to reduce costs. The undercarriage was supplied by Dowty Group, which were furnished with low-pressure tyres. Some Hawks, but not all, were furnished with wheel brakes.

Variants

M.2
Standard production two-seat version, powered by a single 95 hp A.D.C. Cirrus IIIA engine.
M.2A
Cabin version powered by a de Havilland Gipsy III engine, one built.
M.2B
Long-range single-seater powered by an A.D.C Cirrus Hermes IV, one-built.
M.2C
Re-engined with one 120 hp de Havilland Gipsy III engine, one built.
M.2D
Three-seat version with one 95 hp A.D.C. Cirrus IIIA engine, six built.
Hawk Major

The Hawk Major was developed to take advantage of the inverted design of the new de Havilland Gipsy Major engine. Lowering the cylinders below the propeller shaft axis greatly improved pilot visibility and allowed a shorter, lighter undercarriage.

The Hawk Speed Six was a single-seat racing variant of the Hawk Major, with a larger Gipsy Six engine.

Hawk M.2

Hawk Speed Six

The Miles M.11 Whitney Straight was a 1930s twin-seat cabin monoplane designed and produced by the British aircraft manufacturer Miles Aircraft. It was named after Whitney Straight, a Grand Prix motor racing driver, aviator and businessman. The aircraft was the first to combine a side-by-side seating arrangement with an enclosed cockpit for the general aviation sector.

The Whitney Straight was developed after F.G. Miles and Straight recognised that they had similar ambitions to develop modern aircraft suited to flying clubs and private owners alike, and thus decided to collaborate on its production. On 14 May 1936, the first prototype conducted its maiden flight at Woodley Aerodrome; quantity production commenced shortly thereafter. Whitney Straights were used in various roles within the civil market, such as air racing and aerial topdressing.

Approaches were also made by Miles to introduce the Whitney Straight into the military market. While not selected as an army cooperation aircraft for the British Army in the pre-war years, numerous civil aircraft were impressed into military service during the Second World War, the type being largely operated as a communications aircraft. While production ended in 1937, several Whitney Straights remained in an airworthy condition into the twenty first century. A total of 50 aircraft were built.

The Miles M.11 Whitney Straight was a twin-seat monoplane specifically built for use by flying clubs and private owners. Its construction was primarily composed of wood, including spruce frames and three-ply birch covering. The Whitney Straight featured a fixed main undercarriage complete with aerodynamic fairings, along with a fixed tailwheel. Relatively comfortable accommodation for its pilot, a single passenger and their luggage, was provided within an enclosed 'side-by-side' cockpit. The cockpit was covered by a single-piece canopy comprising molded Perspex.

The wings of the Whitney Straight were relatively thick for the era; considerable effort had been put into their design to carefully define their drag properties. The wings were fitted with vacuum-operated split flaps; these were attributed as having enabled the type's relatively low takeoff speed of 50 mph, as well as the aircraft's high rate of climb. An alternative flap arrangement, that was noticeably more efficient and produced less drag while increasing lift coefficient, was experimented with during the later years of the prototype's flying career; it directly influenced the design of several subsequent aircraft.

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

Variants

M.11
M.11B
the sole M.11B was powered by a 135 hp (101 kW) Amherst Villiers Maya I engine, adding 10 mph (9 kn; 16 km/h) to its maximum speed and 200 ft/min (1.0 m/s) to its rate of climb.
M.11C
the sole M.11C was powered by a 145 hp (108 kW) de Havilland Gipsy Major II engine driving a variable-pitch propeller.

The M.3 Falcon was a clean, single engined low-wing monoplane with trousered main undercarriage and fixed tail-wheel, designed in 1934. It was structurally similar to the earlier Miles M.2F Hawk Major family, but had side-by-side seating for two behind the pilot in a glazed cockpit. It was powered by a 130 hp (97 kW) de Havilland Gipsy Major piston engine. The prototype, G-ACTM, built by Philips and Powis first flew at Woodley Aerodrome on 12 October 1934.

The first production aircraft (designated M.3A Falcon Major) was flown in January 1935. It had a wider fuselage than the prototype to improve passenger comfort and revised glazing with a forward sloping windscreen. The M.3A was somewhat underpowered, so the (M.3B Falcon Six) and later versions were fitted with a 200 hp (150 kW) de Havilland Gipsy Six engine.

The M.3C Falcon Six was a four seater with dual controls. The M.3D was strengthened to allow an 11% increase in all up weight compared with the M.3B. The final versions were the M.3E and M.3F.

An enlarged five-seat version was developed as the M.4 Merlin.

The prototype was fitted with extra fuel tanks and entered into the MacRobertson Race from England to Australia in October 1934. It took 27 days to reach Darwin, but returned in a record time of 7 days 19 hours 15 minutes, including one stage of 1,800 miles (2,900 km) non-stop from Jodhpur to Basra.

Pre war, three Falcon Sixes appeared in RAF garb at the Royal Aircraft Establishment (RAE) for trials of a variety of wings and aerodynamic innovations. At the outbreak of the war three aircraft remained civilian as communications aircraft with various companies but, like so many civil aircraft ten others were impressed into service by the Royal Air Force, Royal Navy, the Royal Australian Air Force and the Swedish air force. The RAAF operated 3 Miles Falcons.

Six Falcons survived the war, one of which was used by the RAE to test the wing of the Miles M.52.

Variants

M.3
Prototype three-seat version with a 130 hp de Havilland Gipsy Major engine. 1 built.
M.3A Falcon Major
Production four-seat version with a 130 hp de Havilland Gipsy Major engine. 18 built
M.3B Falcon Six
Three-seat version with a 200hp de Havilland Gipsy Six engine. 11 built, including 1 Falcon Six designated M.3, but not including 2 M.3Bs later converted to M.3E and F.
M.3C Falcon Six
Four-seater with dual controls with a 200 hp de Havilland Gipsy Six engine. 1 built.
M.3D
Strengthened variant with a 200 hp de Havilland Gipsy Six engine. 3 built. One was a converted M.3B.
M.3E
Variant with a 200 hp de Havilland Gipsy Six engine. 1 built but uncertified.
M.3F
A former M.3B modified for Fairey wing, spoiler and retractable aileron trials with the RAE, R4071.[5]
Miles Gilette Falcon
A single aircraft modified for the M.52 program.

The Miles M.28 Mercury was a British aircraft designed to meet the need for a training and communications plane during the Second World War. It was a single-engined monoplane of wooden construction with a twin tail and a tailwheel undercarriage with retractable main units.

Originally, the M.28 had been planned as a replacement for the Whitney Straight and Monarch, but this was shelved when war broke out.

In 1941, the project was revived in response to a requirement for a training and communications aircraft. The design was produced as a private venture by Ray Bournon using Miles' normal wooden construction. The resulting machine introduced several features not found on trainers: retractable undercarriage and trailing edge flaps amongst others. In the communications role, the M.28 had four seats and a range of 500 miles (800 km).

The prototype first flew on 11 July 1941  and proved easy to fly, with light controls and a short landing run. Owing to Miles' heavy commitment to war-production, however, only six aircraft were built, of slightly varying specifications, the last being the Mercury 6 which first flew in early 1946. Examples of the type were operated in the United Kingdom, Denmark, Germany, Switzerland and Australia.

Variants
M.28 Mark I: First prototype – Two seat trainer, powered by 130 hp (97 kW) de Havilland Gipsy Major I engine.
M.28 Mark II: Three seat trainer (with dual controls) powered by 140 hp (100 kW) de Havilland Gipsy Major IIA. One built 1942. Re-engined with 140 hp Blackburn Cirrus Major II and then with a 150 hp (110 kW) Cirrus Major III post-war.
M.28 Mark III: Three seat trainer with triple controls for two students and one instructor, powered by 150 hp Cirrus Major 3 and with revised wing section. One built (PW937).
M.28 Mark IV: Four seat communications aircraft powered by 145 hp (108 kW) Gipsy Major IIA. One built 1944.
M.28 Mark V: Post-war four-seater powered by Cirrus Major III. Square rear windows. One built 1947.
M.28 Mark VI: Post war four-seater powered by Cirrus Major III. Round rear windows. One built 1946.

The Miles M.38 Messenger is a British four-seat liaison and private owner aircraft built by Miles Aircraft.

The Messenger was designed to meet a British Army requirement for a robust, slow speed, low maintenance air observation post and liaison aircraft.

The aircraft designed was a cantilever low-wing monoplane with a fixed tailwheel, powered by the de Havilland Gipsy Major 1D inline engine.

Fitted with retractable auxiliary wing flaps enabling a wing loading of around 12.5 lb per square foot, the Messenger featured triple fins and rudders in order to maintain sufficient controllability down to the exceptionally low stalling speed of 25 mph.

The prototype was converted from a Miles M.28 Mercury and first flew at Woodley on 12 September 1942, some three months after an approach by army officers.[2] When informally test flown by an Aerial Observation Post Squadron it was declared a success, meeting all the army's requirements, however the Ministry of Aircraft Production, having not been consulted, reprimanded George Miles for failing to seek the ministry's permission before rebuilding the aircraft and no orders for the Miles M.38 were placed for the aerial observation post role, AOP units using light, fixed-wing aircraft, notably various marks of Auster.

For more information on the design and development, production and operation, and 11 variants, click here.

The Miles M.17 Monarch was a British, light, touring aeroplane of the 1930s. It was a single-engine, three-seat, cabin monoplane with a fixed, tailwheel undercarriage.

The last civil type produced by Phillips and Powis before the war, the Monarch was a development of their earlier Whitney Straight. Compared to its sibling. the Monarch had an enlarged fuselage, allowing provision of a third seat in part of what had been the luggage space.

Eleven aircraft were built between 1938 and 1939, six of these to British customers, the rest going to export.

On the outbreak of war five of the British-registered machines were impressed by the Air Ministry; one machine belonging to Rolls-Royce acquired camouflage paint but remained in its owner's service. All but one of these survived the war, though a Dutch-registered aeroplane (PH-ATP) was destroyed in the Luftwaffe raid on Schiphol on 10 May 1940. One aircraft, OY-DIO, was on the Danish register until 9 Sept. 1939 and owned by a Dane named Hagedorn.

In the 1950s, one Monarch (G-AIDE) enjoyed some success as a racer in the hands of W.P. Bowles

For the most part, the remaining Monarchs led uneventful but useful careers; a number survived into the Sixties. G-AFJU is displayed at the National Museum of Flight at RAF East Fortune near East Linton, Scotland.

Sporting successes (G-AIDE)
1st - Goodyear Trophy (1957)
3rd - King's Cup Race (1957)
1st - Norton Griffiths Trophy (1958)
2nd - Osram Cup Race (1958)

The Mitchell Kittiwake is a British single engine sporting aircraft designed for amateur building. Plans were available for both single-seat and two-seat versions, but only four were constructed.

Mitchell-Procter Aircraft was set up to produce the Kittwake prototype. This single-seat sports aircraft was a development of the Mitchell-Prizeman Scamp design study that was placed third in the Rollason Midget Racer Competition of 1964. C. G. B. Mitchell was the Kittiwake's designer, with R. G. Procter in charge of building it. The Mitchell-Procter Kittiwake I first flew in May 1967, but about 17 months later the partnership was dissolved and plans for home builders were produced by Procter Aircraft Associates. Mitchell concentrated on the design of a two-seat development, the Mitchell Kittiwake II, with Robinson Aircraft building the prototype. At about the same time Procter Aircraft were designing their own rather larger two-seat Kittiwake I development, the Procter Petrel. Both the two seaters, like the Kittiwake I, were intended for home building. By the time the aircraft first flew, Procter had changed ownership and had been renamed Nash Aircraft Ltd.

The single-seat Kittiwake I monoplane was designed for sports flying and as a glider tug. It is an all-metal aircraft, with low cantilever wings of parallel chord built around a single spar carrying 5° of dihedral. NACA single slotted flaps occupy the whole of the trailing edge inboard of the ailerons. The wings attach to a centre section which is integral with the fuselage, a feature intended to help construction in a small space like a garage. The straight tapered fin carries a horn balanced rudder and the constant chord tailplane has a starboard side trim tab.

The Kittiwake's fuselage is built around four longerons, with flat sides and bottom and single curvature decking. Its overwing cockpit has a rearward sliding canopy and its fixed tricycle undercarriage has cantilever angled steel spring main legs attached to the lower longerons, giving a track of 5 ft 9 in (1.75 m). The Kittiwake I was powered by a 100 hp (75 kW) Continental O-200 flat four engine.

The Kittiwake II differs chiefly in having two side-by-side seating and a more powerful 130 hp (97 kW) Continental O-240. It is longer, heavier and has an increased span which increases the wing area by about 8%. The fuselage is wider and the small dorsal fillet of the Kittiwake I gone; the rudder gained a trim tab and the elevators full width tabs. It first flew on 19 March 1972.

In addition to the prototype, two Kittiwake Is were built, one by Royal Navy apprentices in 1971 for glider towing. For this role a larger diameter (6 ft 4 in, 1.93 m) propeller is fitted, increasing the rate of climb by 24%. A tow release hook is fitted under the tail. Only one Kittiwake II, the prototype, was built.

The Monocoupe 90 was a two-seat, light cabin airplane built by Donald A. Luscombe for Monocoupe Aircraft. The first Monocoupe (Model 5) was built in an abandoned church in Davenport, Iowa, and first flew on April 1, 1927. Various models were in production until the late 1940s.

The Monocoupes were side-by-side two-seat lightplanes of mixed wood and steel-tube basic construction with fabric covering. A braced high-wing monoplane with fixed tailskid landing gear, and the reverse curve rear fuselage lines that were to become one of the signature identifier features of the Monocoupes. The fuselage framework was built up of welded steel tubing in a rigid, triangular-framed Warren truss form for the side panel structures, heavily faired to shape with dural metal sheet formers and wooden fairing strips. The wings were built up of solid spruce spars with wing ribs of basswood webs and spruce cap-strips. The leading edges were covered with dural metal sheet and the entire framework was covered in fabric.

The aircraft was powered originally by either a 60 hp (45 kW) Anzani engine or the unsuccessful 65 hp (48 kW) Detroit Air-Cat radial. The Model 22 was the first light aircraft awarded a type certificate (number 22) and in 1930 it was fitted with the Velie M-5 62 hp (46 kW) five-cylinder radial engine to become the Model 70.

In 1930 Monocoupe introduced the Model 90 with refined lines and a fuselage that was slightly longer and wider, this being sold in Model 90 and Model 90A versions with a 90 hp (67 kW) Lambert R-266 radial engine. The Monocoupe 90 DeLuxe introduced trailing edge flaps, wheel speed fairings and an improved engine cowling. The Model 90AF was fitted with a 115 hp (86 kW) Franklin engine. The Model 90AL had Avco Lycoming engines. The Model 90J was introduced in 1930 with a 90 hp (67 kW) Warner Scarab Jr engine.  

The final two high performance Monocoupe models developed from the Model 90 were the Model 110 with a 110 hp (82 kW) Warner Scarab, and the Model 125 with a 125 hp (93 kW) Kinner B-5 engine. The Monocoupe 110 Special was a clipped wing racing aircraft. The Monocoupe Model 70V of 1932, had the low-powered 65 hp (48-kW) Velie M-5 engine reintroduced to provide more economical operation at the cost of a fall in performance.

In 1941 Monocoupe combined with three other companies to form Universal Molded Products Corp. 20 Model 90AFs were bought by the USAAF, who designated them the Universal L-7, for transfer to the Free French Forces. One was lost during delivery.

Aircraft production halted during World War II, resuming briefly in 1948-1950 under the name Monocoupe Airplane and Engine Corporation. 

The last of this remarkable line of two-seat aircraft was the Monocoupe D-145 of 1934, a high-performance version with a slightly enlarged cabin and powered by a 145 hp (108 kW) Warner Super Scarab engine.

For details of the 15 variants, click here.

The Montana Coyote is an American single-engined two-seat STOL aircraft designed for home building by Montana Coyote Inc. of Helena, Montana.

The Coyote is a high-wing strut-braced monoplane first flown in early 1991 and sold as kit for home building without an engine. With a steel tube fuselage and wooden wings it is designed to take an engine between 100 and 200 hp (74 to 149 kW) as long as it weighs less than 350 lb (159 kg). It has a fixed tailwheel type landing gear with a cabin for a pilot and passenger side-by-side, it is designed to land and take-off within 350 ft (107 m).

The Mooney M-18 "Mite" is a low-wing, single-seat monoplane with retractable, tricycle landing gear.

The Mite was designed by Al Mooney and was intended as a personal airplane marketed to fighter pilots returning from World War II.

The M-18 design goal was extremely low operating costs. The Mite is constructed mainly of fabric-covered wood, with a single spruce and plywood "D" wing spar. The wing aft of the spar is fabric-covered.

The airfoil selected for the design was the NACA 64A215. The M-18 represented the first time a NACA 6-series airfoil had been used on a civil aircraft after World War II.

The aircraft featured a unique "safe-trim" system. This mechanical device links the wing flaps to the tail trim system and automatically adjusts the horizontal stabilizer angle when the flaps are deflected, reducing or eliminating pitch changes when the flaps are lowered.

The Mooney Aircraft Corporation built a total of 283 Mites in Wichita, Kansas, and Kerrville, Texas, between 1947 and 1954. The first seven were powered by belt driven, modified 25 hp (19 kW) Crosley automobile engines, but these proved to be troublesome. Production shifted to the M-18L powered by the four-cylinder, 65 hp (48 kW) Lycoming O-145 powerplant. The original Crosley-powered Mites were recalled and retrofitted with the Lycoming engines at no charge. The later M-18C used the Continental A65 65 hp (48 kW) aircraft engine.

The market for the single-seat M-18 was limited, so Mooney later developed the four-seat M-20 to appeal to aircraft owners with families. In the early 1970s, Mooney offered plans for four different home-built versions of the M-18.

Factory production of the Mite ended in 1954. Leading up to this, the company was losing $1000 on each plane, which accelerated the development of the M20. Another factor was that Continental had ceased production of the engine used in the Mite due to a lack of demand.

A total of 283 Mites were constructed.

The Mooney M10 Cadet is a light airplane manufactured by the Mooney Aircraft Company in 1969 and 1970. The M10 is derived from the ERCO Ercoupe, the type certificates for which Mooney purchased from the Alon Corporation in 1967.

The M10 is similar to the Alon A2-A, and indeed a handful of "Mooney A2-As" were built in Kerrville in 1968 before changeover of Mooney's production line was completed. According to the FAA Type Certificate Data Sheet, the "Model 10 is similar to Model A2-A except for new design empennage, ailerons and fuel tank vent." The most obvious difference is that the M10 replaces the iconic Ercoupe-style dual vertical stabilizer with a tail designed to allow the airplane to spin. Changes to the ailerons, along with replacement of the A2-A's tail, were motivated by Mooney's intent to market the M10 as a trainer: student pilots receiving training in a non-spinnable airplane, as the Ercoupe was, were issued FAA pilot certificates carrying the restriction that they could only fly airplanes which were "characteristically incapable of spinning"; thus the spinnable tail was necessary to turn the A2-A into a general-purpose trainer. Given that they were replacing the tail, Mooney's engineers opted to give it the "backward" profile characteristic of the M20 series. Although the M10's empennage has the same silhouette as the "big Mooneys", it does not swivel the way the M20's does; the Cadet's tail is a conventional design with fixed horizontal stabilizer, hinged elevator, and trim tabs.

The two type certificates that cover all Ercoupe variants, including the Mooney M10, are currently owned by Univair Aircraft Corporation, in Aurora, Colorado, USA.

The M20 was the 20th design from Al Mooney, and his most successful. The series has been produced in many variations over the last 60 years, from the wooden-wing M20 and M20A models of 1955, to the M20V Acclaim Ultra that debuted in 2016. More than 11,000 aircraft in total have been produced.

In November 2008, the company announced that it was halting all production as a result of the late-2000s recession, but would still provide parts and support for the existing fleet. With the injection of Chinese capital after the company's purchase, production of the M20 resumed in February 2014. Since then, the company has released two more M20 models.

With the exception of the earliest models which had wings and tails with wooden frames, M20s are constructed entirely of metal. All are low-wing aircraft, and the wing skin is aluminum. Slotted flaps cover 70% of the trailing edge. Earlier models use a hydraulic hand pump to extend the flaps, while later models have electrically operated flaps. The forward fuselage has a steel-tube cabin structure covered in aluminum skin; the aft portion of the fuselage is of semi-monocoque design. In many places on the skin of the airplane, flush-mounted rivets are used to reduce drag.

For the full details of the various models from 1955 till the company ceased operation in 2019, click here. More than 11,000 aircraft were produced over that time.

The specifications below are for the 2016 M20 Acclaim Ultra.

The Mooney M22 Mustang is the first attempt at a pressurized single engine aircraft by the Mooney Aircraft Company of the United States.

The Mustang was developed to be a top-of-the-line model to supplement Mooney's successful Mooney M20 high-performance light aircraft. It is a five-seat pressurized single-engined aircraft with a wider and longer fuselage than the M20E Super 21 and a taller fin and leading edge fillet. It is a low-winged monoplane with a retractable nosewheel undercarriage, with a similar wing to that used on Mooney's earlier M20 Ranger.

The first prototype flew on September 24, 1964, with the type being certified on September 26, 1966. First deliveries commenced in 1965, continuing until 1970. 36 aircraft were completed before the line was closed. It was produced and sold at a loss, which contributed to the bankruptcy of Mooney.

The "Mark 22" name had previously been applied to a 1957 Mooney M20 experimental aircraft built with twin engines, a nose cone, and an enlarged tail surface. That aircraft did not go into production.

The Model 22, although produced in fairly small numbers, has been operated by private and commercial owners in several countries including the United States and Australia. Its Garrett AiResearch cabin pressurization system gives the equivalent of 11,000 feet (3,400 m) at the aircraft's operational ceiling of 24,000 feet (7,300 m). As a demonstration of its high performance, the second production aircraft was flown non-stop from New York to the Paris Air Show in June 1967, the flight taking 13 hours 10 minutes. The achievement is recorded on the display board in the accompanying photograph. The aircraft had been fitted with an extra fuel tank for the flight. A total of 36 were built. In 2001, 24 aircraft remained in service.

The Mráz M.1 Sokol (English: "Falcon") was a light aircraft built in Czechoslovakia in the years following the end of the Second World War. Designed in secret by Zdeněk Rublič at the Beneš-Mráz factory during the German occupation, the type was put into production in 1946.

The Sokol was a conventional, low-wing monoplane that took the pre-war Beneš-Mráz Bibi as its starting point. Two seats were provided side-by-side in an enclosed cabin, and the main units of the tailwheel undercarriage were retractable. Construction throughout was of wood.

The prototype, designated the M.1/1 and registered as OK-ZHA, first flew on 9 March 1946. After testing, the prototype was redesignated the M.1A, as the type entered production. A re-engined two-seater was built designated the M.1B with a 105 hp (78 kW) ZLAS Toma 4 engine, flying for the first time on 19 May 1946 but no more M.1Bs were built. Instead, the M.1A was modified by adding a third seat in the rear, becoming the M.1C and first flying on 16 February 1947. The M.1C became the main production variant with 183 aircraft built.

In 1948 the M.1C was further developed as the M.1D with an enlarged single-piece canopy and a revised rudder. The M.1D first flew on 4 October 1948 and 104 were built. One M.1D was fitted with locally produced floats and re-designated the M.1E, it first flew in September 1949. A minor variant was the Para-Sokol which was fitted with rearward sliding canopy to allow parachutists to leave the aircraft.

Around 287 aircraft were built but the deterioration of the Urea-based glue used caused many examples to be condemned in the early 1960s and withdrawn from use. Nineteen Sokols were recorded as still being registered in 2013 with only a few still flyable.

Variants

M-1A – original two-seat version with Walter Minor engine
M-1B – similar to M-1A but with ZLAS Toma 4 engine (1 built)

M-1C – revised version, with longer fuselage and third seat, and swept leading edges on wing (183 built)
M-1D – similar to M-1C with new, single-piece canopy and larger rear windows (104 built)

M-1E – similar to M-1D but equipped with pontoons (at least 1 built)

The Mudry CAP 10 is a two-seat training aerobatic aircraft first built in 1970 and still in production in 2007. The plane was developed from the Piel Super Emeraude and was born as the CP100.

The name changed to CAP 10, CAP for 'Constructions Aéronautiques Parisiennes'. The CAP 10 was manufactured by Mudry (name of its designer) in Bernay, France, bought by CAP Industries which then became Apex Aircraft. Following the bankruptcy of Apex in 2008, rights to produce spares were awarded to Dyn'Aviation. After the bankruptcy of DynAero in 2012,[1] manufacture of spares was taken over by CEAPR in Darois.

The prototype C.P. 100 was first flown in August 1968 and was followed by the production variants, the CAP 10 and CAP 10B which had revised tail surfaces. The CAP 10 is a low-wing cantilever monoplane of wooden construction, with the CAP 10C having a carbon sandwich wing spar.

The engine is a 180 hp (130 kW) Lycoming AEIO-360 fuel injection engine, fully lubricated in inverted flight.

300+ aircraft were built, and in 2007 the CAP 10C is still in production as the CAP 10C NG.

The CAP 10 is one of the most successful aerobatic training aircraft in the world. About 200 aircraft are still flying in the late 2000s and nearly two generations of aerobatic champions made their classes with it.

In the late 70's the CAP 10 was developed to the single seater family of the CAP 20, 20L and 21. In the 1980s, a far derivative was the most successful family of the Cap 23x competition single seaters.

Variants

C.A.A.R.P. C.P.100
Prototype aircraft developed from the Piel Emeraude
CAP 10
Initial production aircraft
CAP 10B
Later production aircraft with ventral fin and enlarged rudder
CAP 10C
Improved structure with carbon-fibre wing spar.
CAP 10R

(R for Remorqueur - tower) Prototype of a glider tug version
CAP 10B/K
The exact same model as the CAP 10B modified through the implementation of a modification of the main wing spar approved under "MAJOR REPAIR DESIGN APPROVAL 10045153" by the EASA. This modification has been developed by the French Company Air-Menuiserie in 2013 and allows the CAP 10B/K to recover its flight envelope limitations (Maximum G-Force: +6.5G -4.5G).

The CAP Aviation CAP-23x family is a family of aircraft designed for competition aerobatics. The CAP 230 airframe was a direct development of the CAP 21 competition single seater strengthened to cope with a 300 hp (220 kW) 6-cylinder Lycoming AEIO-540 engine instead of the 200 hp (150 kW) original 4-cylinder Lycoming AEIO-360.

The CAP 230 was primarily developed in 1985 for the French Air Force. From the basic CAP 21 airframe, trailing edge apex triangular surfaces were added to the basic trapezoidal wing and a full wooden construction.[citation needed] It withstood +10/-10 G-forces, had a 270 degrees/second roll rate and a top speed of 400 km/h. Between 1986-1990 this was the mount of the French Air Force aerobatics team (French: Equipe de Voltige de l'Armée de l'Air).

The CAP 231 was developed in 1990. The fuselage design remained unchanged and only leading edge triangular apex surfaces were added to reduce buffeting during high G pullups. The CAP 231 was world champion in 1990. Between 1990-1998 this was the mount of the French Air Force aerobatics team.

To increase performance, in 1991, a carbon-fiber wing taken from an EXTRA 260 (thus the -EX name) was adapted to a few CAP 231 airframes.

The CAP 231EX evolved in 1994. While the fuselage construction retained wood, a carbon-fiber wing was specially designed for durability and light weight. The design has won the World Championships in 1998, 2000 and 2007, as well as a number of other national-level competitions. It has a roll rate of 420° per second and a climb rate of nearly 3,300 feet per minute.

The CAP 232 just like the -230 and -231/-231EX were slightly modified to strengthen the fuselage structure after a fatal accident in 2005 which grounded them for a full year. Fuselage rib n°2 holding the landing gear and the wing spar has been reinforced externally and internally. The planes are now back to competition and came second (individual with a -231EX), sixth with a -232, and first team at the WAC 2007.[3] In the years 1999-2005, examples were flown by the French Air Force aerobatics team.

The Murphy Moose is a Canadian high-wing utility light aircraft produced in kit form by Murphy Aircraft of Chilliwack, British Columbia for amateur construction. The Moose can be purchased as a "quick-build" kit which comes partly pre-assembled.

Builders can choose whether to equip their aircraft with the 269 kW (360 hp) Russian-built Vedeneyev M14P nine-cylinder radial or the horizontally opposed 187 kW (250 hp) Lycoming O-540. Both engines allow the Moose to take off in roughly 180 m (600 ft). Several Moose are equipped with a Pratt & Whitney Canada PT6A-20 turboprop engine, others have installed a 460 hp (343 kW) General Motors LS3 V-8 engine.

The MX2 is a carbon fiber, two seat tandem sport aircraft produced by MX Aircraft of Perth, Western Australia. The MX2 has been used by competitors in the annual Red Bull Air Race World Championship, notably by Australian Matt Hall, as shown above.

The MX2 was based on the Giles G-202 aerobatic trainer, the first prototype was a modified G-202 and first flew in May 2002. The first aircraft of the initial production batch of five first flew in May 2005. The MX2 is a carbon-fibre low wing cantilever monoplane with full span ailerons and a conventional landing gear with a tailwheel. It has an enclosed cockpit for two in tandem on reclining seats and a single piece canopy. The MX2 is powered by a 260 hp (194 kW) Lycoming IO-540 flat-six piston engine with a three-blade tractor propeller. Optimised for aerobatic speed and agility the MX2 can pull a G-load of plus and minus 12 Gs, giving it tight turns and loops and a range of aerobatic maneuvers.

An MX2 raced a Supermarine Spitfire around the Isle of Wight for the 70th anniversary of the first Spitfire produced. The Spitfire won.

g limits: ±12
Roll rate: 420°/s

A short-haul passenger aircraft developed at Myasishchev Design Bureau from 1989 to 2002. The first flight is 1995. Produced at the Nizhny Novgorod aircraft plant "Falcon". Production has been discontinued, 26 aircraft have been produced, of which 4 are prototypes and 22 serial. The aircraft is designed for business aviation and use as an air taxi.

(Above from Google translation of Russian website.)

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 Nesmith Cougar is a light aircraft that was developed in the United States in the 1950s and marketed for homebuilding.

The design, by Robert Nesmith, is a conventional high-wing, strut-braced monoplane with fixed tailwheel undercarriage. The pilot and a single passenger were seated side by side. The fuselage and empennage were of welded steel-tube construction, while the wings were of wood, and the whole aircraft was fabric-covered. Some later aircraft were fitted with a tricycle undercarriage.

The original Cougar design was marketed by Nesmith himself. His intent was to market a low-cost aircraft for homebuilders. He also used the aircraft as a troubled youth project to encourage teens to work together toward a goal. When a modified Cougar won an Experimental Aircraft Association (EAA) design competition in 1963, that organization took over selling plans. Rights to the design were eventually purchased by Acro Sport.

The aircraft shape was influenced by the Beechcraft Staggerwing and Wittman Tailwind. The name came from the college of Nesmith's daughter, the University of Houston, whose athletic mascot is a cougar.