Monoplane

Pro-Fe Banjo

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The Banjo sailplane is of mixed construction. Its 13.3 m (43.6 ft) span wing is strut-braced with one lift strut per side and uses a plywood box spar and spruce wing ribs, with the leading edge of the wing covered in plywood and the rear portion covered in aircraft fabric covering. The nose ribs are expanded polystyrene while the ailerons are made of wood and covered in fabric. The wing airfoil is an SM701 at the wing root transitioning to a Wortmann FX-60-126 at the wing tip, while the tailplane uses a Wortmann FX-71-L-150/30 airfoil. The fuselage is of fibreglass monocoque construction, while its one-piece bubble canopy is made from polycarbonate. The aircraft has fixed monowheel landing gear with a wheel brake and upper wing surface air brakes.

Variants:

Banjo
Unpowered single-seat sailplane with a 13.3 m (43.6 ft) span wing. Four were reported completed and flying in 1998. In production in 2011.

Banjo-MH
Powered version of the Banjo, with a retractable tractor configuration Hirth F33 two stroke 21 kW (28 hp) motor powering a two-bladed wooden propeller. Fuel capacity is 14 litres (3.1 imp gal; 3.7 US gal), gross weight is 260 kg (573 lb) and load limits +4 and -2g. The aircraft has a best glide ratio of 28:1. In production in 2011.

DuoBanjo
Two seats in tandem version, with two side-by-side main wheels mounted in the fuselage and a retractable tractor configuration Rotax 447 two-stroke 30 kW (40 hp) motor powering a ProFe 1.4 m (4.6 ft) two-bladed wooden propeller. Wing span is 16 m (52.5 ft), fuel capacity is 27 litres (5.9 imp gal; 7.1 US gal), gross weight is 460 kg (1,014 lb) and load limits +4.4 and -2.4g. The aircraft has a best glide ratio of 29:1. In production in 2011.

The Banjo wing is based on the SM701 airfoil, trapezoidal outer part is modified into FX-60-126. Wingtips are equipped with winglets. Basic element of the construction is a plywood, box section beam and ribs made from spruce scantlings. Front part of the ribs is made from expanded polystyrene. Leading edge of the wing is covered by plywood and forms a torsion box. Polyester fabric covers trailing part of the wing. On the upper part of the wing are located hinged aerodynamic brakes. Wooden construction ailerons are also covered by a polyester fabric. They are operated via Dural tube rods. Wings are supported by shaped struts. Wing is fixed to the fuselage by mountings located on the wing beam and on the trailing edge section.

Fuselage, including the tail fin, is formed from a fiberglass monocoque. Monocoque is reinforced by plywood ribs. Ribs are utilized as wings, struts, undercarriage wheel and rescue system mountings.

Cockpit (closed type) is covered by a one-piece canopy made from a splinter-proof polycarbonate (Makrolon). There is a ventilation window on the side of the canopy. Control stick is a classic style type. The cockpit is equipped with aerodynamic brakes lever (left side), rope release control (“T” shaped handle on the instrument panel) and trim handle. The cockpit is ventilated via ventilation outlets, located on the instrument panel. Adjustable pilot’s seat is equipped with 4-point safety belts.
The Banj MH Cockpit has engine throttle (left side), power unit position selector, ignition switch, starter, propeller stop control and main power switch (on the right side of the cockpit).

Fixed undercarriage consists of the main unsprung wheel (outer radius 400mm) and uncontrollable tail wheel (outer radius 140mm). The main wheel is fitted with a disk brake. The brake is operated via a cycle brake lever, mounted on the control stick.

Tail surfaces are “T” shaped. Horizontal tail surfaces have similar construction as the wing and use modified Wortmann FX-71-L-150/30 airfoil.

Controls and instrumentation. The instrument panel of the plane is equipped with the following instruments: airspeed indicator, combined electronic altimeter/variometer, compass and bank indicator. The Banjo MH instrument panel also has RPM gauge, fuel gauge, and engine temperature gauge. Power unit management panel is located on the right side of the cockpit. Instrumentation can be customized according to customer’s requirements.

The DuoBanjo is equipped with one instrument panel, containing following instruments: airspeed indicator, altimeter, variometer, RPM gauge, fuel gauge, engine temperature gauge, compass and bank indicator. Power unit management panel is located on the right side of the cockpit.

System of controls. Ailerons and elevator are operated via rods, equipped with swiveling joint ends. Levers are fitted with ball bearings. Rudder is cable controlled. Aerodynamic brakes are also cable controlled, in combination with springs. The DuoBanjo is equipped with dual set of controls, however lifting/retracting of the power unit can be controlled only from the front seat. Control sticks are classic style type. Seats are equipped with 4-point safety belts.

The powered Banjo power unit is based on the engine HIRTH F33 B, equipped with an electric starter, belt reducer and two-blade propeller. Power unit can be lifted or retracted into the enclosed power unit bay during the flight.

Fuel system. Alu fuel tank is located in the fuselage and it can contain 14 liters of the fuel. It is equipped with fuel float system, measuring quantity of the fuel in the tank. Filler neck is located on the left side of the fuselage, below the wing. The DuoBanjo has 27 liters of the fuel.

Electrical system. The main source of the energy is an on-board accumulator 12V-14Ah, which is recharged by the engine. The accu feeds the lifting/retracting system of the power unit together with the electric starter.

Specifications:

Banjo
Wing span: 13,3 m
Length: 6,3 m
Wing area: 10,5 sq.m
Main undercarriage wheel diameter: 400 mm
Tail wheel diameter: 140 mm
MTOW: 220 kg
Load factor: +4,4/-2,2 G
Max. speed VNE: 140 km/h
Max. speed in turbulence VB: 110 km/h
Stall speed: 50 km/h
Min. sink: 0,68 m/s
L/D: 28
Number of seats: 1

Banjo-MH
Wing span: 13,3 m
Length: 6,3 m
Wing area: 10,5 sq.m
Main undercarriage wheel diameter: 400 mm
Tail wheel diameter: 140 mm
MTOW: 260 kg
Load factor: +4/ -2 G
Max. speed VNE: 135 km/h
Max. speed in turbulence VB: 110 km/h
Stall speed: 60 km/h
Min. sink: 0,86 m/s
L/D: 28
Climb performance with MTOW: + 2m/s
Fuel tank capacity: 14 liters
Number of seats: 1

DuoBanjo
Engine: Rotax 447 UL DCDI 1V, 29 kW (6500 rpm)
Propeller: ProFe 1400mm
Wing span: 16 m
Length: 7,35 m
Height (propeller in retracted position): 1,57 m
Wing area: 13,86 sq.m
Aspect ratio: 18,3
Wing load at 460kg: 33 kg/sq.m
Number of seats: 2
Empty weight: 250 kg
MTOW: 460 kg
Max. weight of the crew: 200 kg
Min. pilot’s weight: 70 kg
Stall speed: 64 km/h
Maneuver speed Va: 130 km/h
Max. speed in turbulence Vb: 130 km/h
Max. speed Vne: 175 km/h
Min. sink (at 90 km/h): 0,9 m/s
Best L/D (at 100 km/h): 29
Cruise speed (5000 rpm): 110 km/h
Max. climb: 3 m/s
Load factor: + 4.4 / – 2.4 G
Fuel consumption, cruise: 9.5 l/h
Fuel tank capacity: 26 liters

Banjo
Banjo MH

Proctor Coogee

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Designed and built by Tom Proctor in Australia during 1940-41, The Coogee is essentially a scaled up Hutter 17 hlider.

Registered VH-GFD, Tom Proctor made about 200 short flights in it from 1942 to 1945 and it was then sold to the Victorian Motorless Flight Group. In 1956 ownership changed to the Geelong Gliding Club and subsequently in 1963 it was acquired by E.J. Williams and F.G. Wyer who undertook a thorough overhaul and a complete re fabric of it.

It was then sold to G.C. Curtis, F.O. Connell and R.T. Harris in 1966 who retired it from service 1967 after a total of 3,851 flights and 415 Hours.

The Coogee was donated to a museum by the C. Curtis/G. Downs estate, and restored to display condition.

Proctor Kittiwake I / Mitchell-Proctor Kittiwake I

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G-ATXN Mitchell-Procter Kittiwake

Originally designed in 1964-65 by R. G. Proctor and C. G. B. Mitchell as a dedicated single-seat glider tug aircraft. Mitchell-Procter Aircraft was set up to produce the Kittwake prototype. It was a development of the Mitchell-Prizeman Scamp design study of 1964. ‘Kit’ Mitchell was the Kittiwake’s designer, with Roy Procter in charge of building it. It had excellent visibility, sturdy landing gear.

The Kittiwake was of all-metal stressed skin construction with tricycle landing gear. The nose-wheel was steerable for taxiing and the aircraft was fitted with hydraulic brakes.

Mitchell-Proctor Kittiwake Under Construction 1 Jan 1967

The aircraft would be capable of aerobatics with a rate of Roll 200 degrees at 103 mph (90 kn; 166 km/h). The Kittiwake had a rate of climb of 700 feet (213 metres) per minute with a 1,000 lb (454 kg) glider in tow.

The single-seat Kittiwake I 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 engine.

The wing had generous flaps with high operating speeds which allowed for a fast descent. It had a self-starter system, provision for a radio. The Kittiwake also had a mechanism for retracting the tow rope during the descent. This design was fully aerobatic and additional fuel tanks could be fitted to extend the range.

Mitchell-Proctor Kittiwake Under Construction 1966

By the middle of 1965 production tooling were being made for the wing ribs as well as spars machined.

The Kittiwake single-seat, low-wing monoplane was designed to make full use of all-metal materials and modern construction while retaining a simplicity of design that lends itself to homebuilding.

Mitchell-Proctor Kittiwake I G-ATXN Cranfield 22 Jun 2002

The prototype was started at Camberley but completed by BEA Engineering in 1966-7, powered by a Continental O-200-A. First flown at Lasham on 23 May 1967, it was registered G-ATXN PFA.1306. It was re-engined with a fan-cooled Lycoming O-290 at Lasham in 1972. The prototype was later known as the Mitchell-Procter Kittiwake I. Around a year and a half later the partnership was dissolved and plans for home builders were produced by Procter Aircraft Associates.

A second was built at RNAS Lee-on-Solent as an apprentice project under Lieutenant Commander Cudmore, started in 1969. First flying on 21 October 1971 sn serial XW784, at Lee-on-Solent, powered by a Rolls-Royce/Continental O-200-A.

It was subsequently registered G-BBRN. Built, one by Royal Navy apprentices in 1971 for glider towing, 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.

In later years the prototype was re-engined with a Lycoming O-290-D2 engine.

Mitchell continued development and produced the Mitchell Kittiwake II two-seater. Plans were available for both single-seat and two-seat versions, but only four were constructed. Examples built of the Kittiwake I: G-AXTN, G-BBRN (marked as XW784).

One Kittiwake was active until at least at 2005 and the other is still active. They remain on the UK Civil Register. These are the prototype, G-ATXN and the ex-Naval G-BBRN. The latter is painted, as in its Naval days, as XW784.

Gallery

Kittiwake I
Engine: 1 × Rolls Royce-Continental O-200-A, 100 hp (75 kW)
Propeller: 2-bladed McCauley 69CM52, 5 ft 9 in (1.75 m) diameter metal, fixed pitch
Wing span: 24 ft 0 in (7.32 m)
Wing area: 105 sq ft (9.8 m2)
Length: 19 ft 7 in (5.97 m)
Height: 7 ft 6 in (2.29 m)
Empty weight: 910 lb (413 kg)
Gross weight: 1,250 lb (567 kg) for aerobatic flight
Maximum take-off weight: 1,350 lb (612 kg)
Fuel capacity 26 USG
Maximum speed: 131 mph (211 km/h; 114 kn)
Cruise speed: 122 mph (106 kn; 196 km/h) at 75% power
Stall 48 mph
Range: 540 miles (469 nmi; 869 km) at 92 mph (148 km/h)
Ferry Range with additional tanks: 600 miles (521 nm; 966 km)
Rate of climb: 850 ft/min (4.3 m/s)
Crew: 1

Pro-Composites Personal Cruiser

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The Personal Cruiser currently uses a Corvair automotive engine converted for aircraft use, and is designed for an installed engine weight of up to 250lbs and from 65-115 hp. The Personal Cruise has a 29″ wide cabin.

The 2009 airframe kit price was $9,710. In the air complete from $18k to $25k.

Engine: Corvair 2700cc, 100 hp
Hp range: 60-120
Wing area: 76.5 sqft
Span: 25.5 ft
M.A.C: 36 in
Airfoil: Eppler
Aspect Ratio: 8
Dihedral: 6 degrees
Length: 17’ 4”
Empty Weight: 650 – 750 lbs
Useful Load: 500 lbs
Gross Weight: 1250 lbs
Fuel Load: 12-18 US Gallons
Vne: 212 mph
Va: 147 mph
Econ. Cruise power: 116 mph @ 2.5 gph
High Cruise: 150 mph @ 4.8 gph
Rate of Climb: 700-1800 feet/min
Stall: 58 mph (Clean)
Load factor: +4.5g/-3.0 at 1250lbs
Take-off / Landing: 400 ft/ 350ft
Cockpit Width: 29” interior dimension
V-tail Area: 16 sqft
V-tail Span: 6.125 ft
V-tail Airfoil: Eppler
Landing Gear: Fixed Tri-gear w/castering nose wheel

Pröckl & Hasselböck Motorschwingenflieger / Flügelschlagflieger

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The Motorschwingenflieger / Flügelschlagflieger designed by Moritz Hasselböck and Wilhelm Pröckl, and apparently worked on for five years in Vienna, was completed about 1908. The construction of the machine reveals that the flapping wings were not only just flapping in a vertical plane. Pröckl & Hasselböck had realized that in this way the ornithopter would only ascend and descend vertically. To achieve forward motion they devised a method to rotate the wings to another angle with the objective to achieve forward motion or in the event of landing, a braking of the speed of descent.

The machine was built to specification by “Automobilfirma Wyner, Huber und Reich” of Vienna. Photos taken on the property of the firm date from July 1908.

PROCAER Cobra F.400 / F.480

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In 1960, under the direction of Stelio Frati, Procaer built the F.400 Cobra, a two-seater jet powered by a Turbomeca Marboré II.

Construction of Cobra is mixed wood and all metal and the outer coating of birch plywood covered with a pure aluminum foil bonded over the entire surface.

The prototype was destroyed during its return from the Paris Air Show to Italy.

A second prototype, with four seats and a Marboré VI, the Procaer F-480, was maintained in the collection of Charles Bezard.

Engine: Turbomeca Marboré II
Wingspan: 8.70 m
Length: 7.80 m
Height: 2.80 m
Wing area: 11.70 m²
Aspect ratio: 6.5
Empty weight: 700 kg
Loaded weight: 1300 kg
Wing loaded: 111 Kg / m²

Pritchard Rocket Air Ship

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Charles Pritchard of Emporia, Virginia, was a railroader by profession, set out to build an all-aluminium wingless combined aircraft/car which had been ten years in the making.

The Rocket Air Ship plane has short baffles or fins in place of wings, a 90 hp engine, a conventional propeller and tail assembly and a tricycle landing gear. It was 21 feet long, 98 inches wide and weighed 800 lbs.

The body of the plane is made entirely of aluminium. Each side has baffles (or fins) of varying length. The fins “hold air in the proper channel over the hull of the ship to give the hull its lift”.

Ailerons for changing direction in flight are on the sides of the plane. Conventional equipment on the wingless craft includes a tricycle landing gear, metal propeller, 90 hp engine and flight instruments.

Built for less than $1500, Pritchard was helped in the construction by Billy Davis of Emporia.

“Charles Pritchard, designer builder and pilot, makes first test of his wingless Rocket Air Ship on mile lone runway at Emporia, Virginia, airport.

Plane has short baffles or fins in place of wings, 90 hp engine, conventional propeller and tail assembly, tricycle landing gear, is 21 feet long 98 inches wide weighs 800 lbs. Pritchard made eight runs along runway, but didn’t; get off the ground. Says he’ll make modifications and try again.” (circa 1955)

Primac Tukan

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The Tukan features a composite fuselage and fabric covered wood wings. Air brakes are fitted on the upper wing surface. The engine can fold back to inside the fuselage.

Engine: Rotax 447, 40 hp
Wing span: 14.7 m
Wing area: 14.7 sq.m
MAUW: 420 kg
Empty weight: 215 kg
Fuel capacity: 32 lt
Max speed: 125 kph
Cruise speed: 85 kph
Minimum speed: 60 kph
Climb rate: 2 m/s
Fuel consumption: 8 lt/hr
Seats: 2