1 engine

Neukom AN-22

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Single seat single engined high wing mono¬plane with conventional three axis control. Wing has unswept leading edge, swept for¬ward trailing edge on outboard half of span, and tapering chord; conventional tail. Pitch control by elevator on tail; yaw control by fin mounted rudder; roll control by half span ailerons; control inputs through stick for pitch/roll and pedals for yaw. Wing braced from below by struts; wing profile NACA 4415; double surface. Undercarriage has three wheels in tricycle formation with addi¬tional tailskid; no suspension on nosewheel and rubber suspension on main wheels. Push right go right nosewheel steering con¬nected to yaw control. Brakes on main wheels. Aluminium tube framework with optional pod. Engine mounted below wing driving pusher propeller.

The AN 22 was designed by the Swiss Albert Neukom who also built the first two examples to obtain certification in West Germany. The AN 22 made its first flights in March 1983 and was shown in the same month at the Aero 83 exhibition at Friedrichshafen. Point Aviation acquired the licence to build and sell this machine throughout the world, the first production machines being built in spring 1983. The model makes use of the original formula tried by Albert Neukorn in 1982 on the prototype AN 20, whereby the three¬cylinder Konig 430 cc engine is carried behind the wing on a mount coming from the large diameter spar which carries the tail. This spar also acts as the axis of the propeller which is driven through a triple V belt reduction drive. The two blades can fold backward parallel to the spar.

Production versions were factory built and sold by Point Aviation in West Germany.

Neukom completed the construction (May 1983) of the AN 22 Twin, a two seater version of the AN 22.

AN-22
Length overall 18.4 ft, 5.60 m
Height overall 4.3ft, 1.30m
Wing span 33.511, 10.20m
Chord at root 3.9ft, 1.20m
Chord at tip 3.3ft, 1.00m
Dihedral 4 degrees
Sweepback 0 degrees
Tailplane span 8.5 ft, 2.60 m
Fin height 3.1 ft, 0.95 m
Total wing area 126 sq.ft,11.8 sq.m
Total aileron area 12.1 sq.ft, 1.12 sq.m
Fin area 6.6 sq.ft, 0.61 sq.m
Tailplane area 11.7sq.ft, 1.09sq.m
Total elevator area 6.5 sq.ft, 0.60sq.m
Wing aspect ratio 8.9/1
Wheel track 6.2 ft, 1.90 m
Nosewheel diameter overall 10 inch, 26cm
Main wheels diameter overall 12 inch, 30 cm
Engine: Konig SC430, 22hp at 4200rpm
Propeller diameter 52 inch, 1.32 m
Belt reduction, ratio 1.8/1
Max static thrust 143 lb, 65 kg
Power per unit area 0.17 hp/sq.ft, 1.9 hp/sq.m
Fuel capacity 5.3 US gal, 4.4 Imp gal, 20.0 litre
Empty weight 232 lb, 105 kg
Max take off weight 464 lb, 210kg
Payload 232 lb, 105kg
Max wing loading 3.68 lb/sq.ft, 17.9 kg/sq.m
Max power loading 21.1 lb/hp, 9.5kg/hp
Load factors +6.0, 3.0 ultimate
Max level speed 75 mph, 120 kph
Never exceed speed 81 mph, 130 kph
Max cruising speed 56 mph, 90 kph
Economic cruising speed 44 mph, 70 kph
Stalling speed 24 mph, 40 kph
Max climb rate at sea level 600 ft/min, 3.1 m/s
Min sink rate 200 ft/min at 32 mph, 1.0 m/s at 52 kph
Best glide ratio with power off 14/1 at 34 mph, 55 kph
Take off distance 330 ft, 100 m
Land¬ing distance 260 ft, 80 m
Range at average cruising speed 124 mile, 200 km

AN-22 Twin

Neukom AN-21 / AN-21R

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AN-21R

Single seat single engined high wing monoplane with conventional three axis control. Wing has swept forward leading and trailing edges, and tapering chord; no tail, canard wing. Pitch control by elevator on canard; yaw control by tip rudders; roll control by one-third span ailerons; control inputs through stick for pitch/roll and pedals for yaw. Wing braced from below by struts; wing profile Wortmann FX63 137; double surface. Undercarriage has three wheels in tricycle formation; no suspension on nosewheel and glassfibre suspension on main wheels. Push right go right nosewheel steering connected to yaw control. Brakes on nosewheel. Aluminium/tube/fabric fuselage, totally enclosed. Engine mounted at wing height driving pusher propeller.

1980 Wasserkuppe, piloted by Klaus Richter

As Albert Neukorn comfirmed, this machine was never intended for production. In fact, he wanted to design a single seater canard aircraft, as much to try out this formula as for his own pleasure. Of hybrid technology (Duralumin tubular structure with composite materials for the wing, the canard and rudders), the prototype made its first flights in 1980 and remains unique, with no direct descendants. It was originally called the AN 21. Later it was sold to a German purchaser, Klaus-Jurgen Richter, who flew it in the London to Paris in September 1982, and so the aircraft is now called the AN 21R, this last letter referring to Mr Richter himself.

1980 Wasserkuppe, piloted by Klaus Richter

Length overall 16.1 ft, 4.90 m
Height overall 7.9 ft, 2.40 m
Wing span 41.3 ft, 12.60 m
Mean chord 2.8 ft, 0.85 m
Canard span 9.8 ft, 3.00m
Canard chord 1.7ft, 0.53m
Total wing area 132 sq.ft, 12.3 sq.m
Main wing area 115sq.ft, 10.7 sq.m
Canard area 17 sq.ft, 1.61sq.m
Main wing aspect ratio 14.8/1
Engine: Konig SC430, 25 hp at 4200 rpm
Power per unit area 0.19 hp/sq.ft, 2.0 hp/sq.m
Max level speed 81 mph, 130kph
Stalling speed 26mph, 42 kph
Max climb rate at sea level 500 ft/min, 2.5 m/s

Neukom AN-20

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AN-20B

Single seat single engined high wing monoplane with conventional three axis control. Wing has unswept leading and trailing edges, and constant chord; T tail. Pitch control by elevator on tail; yaw control by fin mounted rudder; roll control by one third span ailerons; control inputs through stick for pitch/roll and pedals for yaw. Wing braced from below by struts; wing profile Wortmann FX 63 137; double surface. Undercarriage has three wheels in tricycle formation with tailskid; no suspension on nosewheel and glass fibre suspension on main wheels. Push right go right nosewheel steering connected to yaw control. Brakes on main wheels. Glass fibre fuselage, partially enclosed. Engine mounted at wing height driving pusher propeller. Wing and T tail have wood spars, ribs in styrofoam and covered with expoxied glass fibre.

His first microlight made its first flights in 1978, the prototype AN 20 using a T tail carried on a Kevlar spar of round section. Connected to the fuselage at the same height as the wing, the tubular fuselage carried basically a mono wheel undercarriage but with an additional nosewheel steerable from the rudder bar, the main wheel being positioned directly below the wing. Moreover, the vertical fin below the fuselage spar was provided with a tailwheel in line with the other two.

This machine was shown in various publications under the designation of AN 20M, which was a great surprise to Albert Neukorn, who tells us that he had never called this first model by any other name than AN 20, except that it eventually became AN 20A to distinguish it from the later AN 20B. The prototype was shown at the European homebuilders meeting at Brienne in July 1982.

The AN 20B is directly evolved from its predecessor whose rectangular plan form wing it has retained, supported by a profiled strut under each half wing. A significant change is the inclusion of air brakes, while the AN 20B is provided in addition with an elegant glass fibre fairing with windscreen encompassing all the forward section of the fuselage as far as the trailing edge of the wing, where it joins the spar carrying the tail. Another important difference from the AN-20A is that this spar is no longer level with the wing but mid mounted, a change which required a re design of the T tail. As a result, the fin and rudder no longer continue below the spar. The engine, previously fitted below the spar is now carried by a tubular structure above the rear spar, effectively level with the wing. Production models use the three cylinder Konig SC430 driving a three bladed pusher propeller. Finally, a last important modification, the AN 20B replaced the single main wheel undercarriage of the AN 20A with a tricycle undercarriage whose main wheels are fitted with drum brakes.

The AN 20B was still produced by Albert Newkom himself in 1983, either ready to fly ex works without engine or as a set of plans. An attempt to set up production facility in France with the AN 20B in 1981 has been abandoned.

Length overall 17.7 ft, 5.40 m
Height overall 3.9ft, 1.20m
Wing span 41.3ft, 12.60m
Constant chord 2.611, 0.80m
Dihedral 2 degrees
Sweepback 0 degrees
Tailplane span 8.0ft, 2.45m
Fin height 3.2ft, 0.95m
Total wing area 109sq.ft, 10.1sq.m
Total aileron area 8.5 sq.ft, 0.79 sq.m
Fin area 6.6 sq.ft, 0.61 sq.m
Tailplane area 8.4 sq.ft, 0.78 sq.m
Total elevator area 4.2 sq.ft, 0.39 sq.m
Wing aspect ratio 15.8/1
Wheel track 4.7ft, 1.43m
Nosewheel diameter overall 8 inch, 21 cm
Main wheels diameter overall 8.5 inch, 22cm
Engine: Konig SC430, 24 hp at 4200 rpm
Propeller diameter 42 inch, 1.06 m
Belt reduction, ratio 1.8/1
Max static thrust 121 lb, 55 kg
Power per unit area 0.22 hp/sq.ft, 2.4 hp/sq.m
Fuel capacity 5.3 US gal, 4.4 Imp gal, 20.0 litre
Empty weight 287 lb, 130 kg
Max take off weight 508 lb, 230 kg
Payload 221 lb, 100 kg
Max wing loading 4.68 lb/sq.ft, 22.8 kg/sq.m
Max power loading 21.2 lb/hp, 2.4kg/hp
Load factors; +5.3, 2.6 ultimate
Max level speed 93 mph, 150 kph
Never exceed speed 99 mph, 160 kph
Max cruising speed 68 mph, 110 kph
Economic cruising speed 59 mph, 95 kph
Stalling speed 31 mph, 50 kph
Max climb rate at sea level 500 ft/min, 2.5 m/s
Min sink rate 160 ft/min at 37 mph, 0.80 m/s at 60 kph
Best glide ratio with power off 18/1 at 37 mph, 60 kph
Take off distance 360 ft, 110 m
Land¬ing distance 330 ft, 100m
Service ceiling 11,500 ft, 3500 m
Range at average cruising speed 186 mile, 300km

Nessunov Ju-87B-2

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Russian registered RA-0565G is an approximately 75% scale Ju-87B-2 owned by Vladimir Nessunov and first flown on June 20, 2000.

This machine is apparently stationed at the Kubinka test base and is flown by the Kublinka Aeroclub there.

In Moscow – at Zhukovsky for MAKS 07

Engine: 210Hp Walter (LOM) M337.
Wingspan: 14.94 m

Nesmith Cougar / Cougar Comet / Chigger / Landoll’s Skydoll

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Cougar 1

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 with dual controls. The fuselage and empennage were of welded steel-tube construction, while the wings were of wood, and the whole aircraft was fabric-covered. Continental engines of C75, C85 and C90 can be used.

The first, N75282, first flew in March 1957.

With a redline speed of 195 mph, the Cougar maintains a brisk cruise of 120 to 165 mph, depending on choice of engine which can range form 65 hp to 125 hp. Landing approach is done at 80 mph and touchdown is around 70.

Cougar C-1 by Warren Croace

The original Cougar design was marketed by Nesmith himself. The design was modified by Leonard Eaves for an EAA design contest in 1963, principally for the purpose of including folding wings. When the 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 can be towed to and from the airport on its own landing gear.

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.

Variants:

Nesmith Cougar
The original design for home building

Nesmith Cougar Comet
Cougar modified with a 125hp Lycoming O-290D.

Nesmith Chigger & Landoll’s Skydoll
One example was built with folding wings and Culver Cadet landing gear, called the “Chigger”. Another example built with folding wings with automatic control latching.

Variation:
Eaves Cougar 1

Engine: Lycoming O-235, 115-hp (86 kW)
Wingspan: 20 ft 6 in (6.25 m)
Wing area: 83 sq.ft (7.71 sq.m)
Aspect ratio: 5.06
Length: 18 ft 11 in (5.77 m)
Height: 5 ft 6 in (1.68 m)
Empty weight: 624 lb (283 kg)
Gross weight: 1,250 lb (567 kg)
Fuel capacity 25 USG
Maximum speed: 195 mph (314 km/h)
Cruise 166 mph
Stall 53 mph
Climb rate 1300 fpm
Service ceiling: 13,000 ft (3,950 m)
Takeoff run 450 ft
Landing roll 350 ft
Range: 750 miles (1,200 km)
Seats: 2

Engine: Continental C-85, 80 hp
Speed max: 195 mph
Cruise: 135 mph
Range: 600 sm
Stall: 53 mph
ROC: 1000 fpm
Take-off dist: 800 ft
Landing dist: 700 ft
Service ceiling: 16,000 ft
HP range: 65-125
Fuel cap: 25 USG
Weight empty: 624 lb
Gross: 1250 lb
Height: 5.5 ft.
Length: 18.9 ft
Wing span: 20.5 ft
Wing area: 82.5 sq.ft
Seats: 2
Landing gear: tail wheel

Némethy Flugrad / Flying wheel

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Flying wheel no.2

Designed and built by Emil von Némethy at his factory in Arad, Hungary (now in Romania). The construction of his Flugrad (“flying wheel”) started sometime in 1899 yet wasn’t completed until 1901. A second machine appeared in 1903 – pictured in a 1907 Scientific American article – and in 1910 produced a third and final original design. Némethy soon after however, gave up his experiments once his Anzani motor was damaged and he’d run out of money.

Nemeth Umbrellaplane / Roundwing

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Initial experiments by Nemeth with rotating wingforms go back to 1929. In 1934 Nemeth designed, and students at Miami University (OH) built the Umbrellaplane / Roundwing.

A two place monoplane featuring a circular wing on a lengthened Alliance Argo fuselage for STOL performance, to test circular wing configuration.

The sole example, NX13651, was powered by a 90hp Lambert, later repowered with a 120hp Warner Scarab, and later reworked as a divided wing. Name has been seen spelled Nuneth.

Wingspan: 16’0″
Length: 20’0″
Max speed: 120 mph
Cruise speed: 95-100 mph
Stall: 20-25 mph
Seats: 2