Aircraft

Applebay Zia

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The Zia was originally conceived as a tailless motor glider and transformed by Oshkosh 1983 into the twin-boom pusher.

George Applebay entered the ultralight world with a very soaring oriented design, the Zia, whose control system consists of tip rudders, angled so that they work in roll as well as yaw and controlled by stick and pedals through a mixer, and a slotted flap occupying 25% of the canard surface, which provides pitch control. Glidepath control is by flaps which extend to 45 degs.
The tricycle undercarriage has a steerable nosewheel and the braked main wheels are suspended on glass fibre struts reinforced with Kevlar. He designed the Zia according to the JAR22 standard, using composite construction in the main but with Dacron wing covering.
Single seat single engined mid 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 flaps on canard; yaw/roll control by angled tip rudders; control inputs through stick for pitch/yaw/roll and pedals for yaw/roll. Cantilever wing; wing profile; double surface. Undercarriage has three wheels in tricycle formation; suspension on nosewheel and glass fibre/Kevlar suspension on main wheels. Flush right go right nosewheel steering connected to yaw control. Brakes on main wheels. Composite construction fuselage, totally enclosed. Engine mounted at wing height driving pusher propeller. The engine is started by a pull rope either on the ground or for air starting.

Engine: Robin EC25PS, 18 hp.
Power per unit area 0.14 hp/sq.ft, 1.6 hp/sq.m.
Fuel capacity 4.0 US gal, 3.3 Imp gal, 15.0 litre.
Length overall 13.1ft, 4.00m.
Wing span 43.3ft, 13.20m.
Total wing area 125sq.ft, 11.6sq.m.
Empty weight 209 lb, 95kg.
Max take off weight 452 lb, 205kg.
Payload 243 lb, 110kg.
Max wing loading 3.62 lb/sq.ft, 17.7 kg/sq.m.
Max power loading 25.l lb/hp, 11.4kg/hp.
Never exceed speed 81 mph, 130kph.
Cruising speed 59mph, 95 kph.
Stalling speed 28 mph, 45 kph.
Best glide ratio with power off 27/1 at 42 mph, 67 kph.
No. of Seats: 1

Wing span: 14m / 46ft
Wing area: 118 sq.ft / 10.96 sq.m
Empty Weight: 182kg / 400lb
Payload: 113kg / 250lb
Gross Weight: 295kg / 650lb
Wing Load: 26.92kg/sq.m / 5.5lb/sq.ft
Aspect ratio: 18
Airfoil: Wortmann FX 66-197
Structure: fiberglass, carbon spar

Applebay Zuni / Aero Tek Model V

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Designed and built by the New Mexico-based firm of Aero Tek under the direction of George Applebay, the Zuni, previously known as the Aero Tek Model V Zuni.

The single-seat 15-meter Zuni, which first flew on 18 November 1976 in New Mexico, was in limited production from 1977 until 1983.

It is sailplane of conventional layout, with a flush transparent canopy and a T-tail. It made its first fight on 18 November 1976, and is of glassfibre construction overall. The cantilever shoulder-mounted wing has a Wortmann wing section developed at the Akaflieg Stuttgart and has full-span camberchanging flaps and ailerons. The flaps and ailerons may be operated separately or interconnected. There is provision for up to 180kg (397lb) of water ballast in the wing, and the undercarriage consists of a single monowheel with a tail bumper fairing under the fin; the forward fuselage tapers to a slimmer boom section carrying the tail unit, and the wings have rectangular inner sections and tapered outer panels.

The fuselage features a roomy cockpit with a semi-reclining seat and in-flight adjustable rudder pedals under a large one-piece canopy. The controls for flaps and landing gear are mounted on the left-hand side of the cockpit, with a side-mounted control stick on the right. The all-moving tailplane is trimmed with a press-button on the control stick.

The two-piece high-set wings contain control linkages which engage automatically when the sailplane is rigged. The interconnecting flaps and ailerons extend the full span of the wings. Flaps can be lowered to +90° for landing or for use as airbrakes. The landing gear consists of a large manually operated retractable monowheel, designed to withstand landings at maximum weight including water ballast, and a tail wheel.

The Zuni II model has carbon spar caps and optional carbon control surfaces, and water ballast capacity is increased to 219 kg. / 483 lb.

Aero-Tek Model V Zuni
Length: 22.047 ft / 6.72 m
Height: 4.265 ft / 1.3 m
Wingspan: 49.213 ft / 15.0 m
Aspect ratio: 22.2
Wing area: 108.716 sq.ft / 10.1 sq.m
Height: 4 ft 8in
Max take off weight: 959.2 lb / 435.0 kg
Weight empty: 493.9 lb / 224.0 kg
Max. speed: 157 kts / 290 km/h / 207mph (in smooth air)
Min sinking speed: 1.71 ft/sec at 50mph
Landing speed: 37 kts / 68 km/h
Cruising speed: 45 kts / 84 km/h
Wing load: 8.82 lb/sq.ft / 43.0 kg/sq.m
Crew: 1

Zuni II
Wing span: 15m / 49.2ft
Wing area: 10.13sq.m / 109sq.ft
Empty Weight: 238kg / 525lb
Payload: 306kg / 675lb
Gross Weight: 544kg / 1000lb
Wing Load: 53.7kg/sq.m / 11.01lb/sq.ft
Water Ballast: 220kg / 483lb
L/DMax: 38@ 98 kph / 53 kt / 61 mph
Aspect ratio: 22
MinSink: 0.55 m/s / 1.8 fps / 1.07 kt
Airfoil: Wortmann mod.
Structure: all fiberglass
No. of Seats: 1

Applebay Zuni
Wing span: 15.0 m (49 ft 2 l/2 in)
Length: 6.71 m (22 ft 0 in)
Height: 1.3 m (4ft 3 in)
Wing area: 10.13 m 2 (109.0 sq ft)
Wing section: Wortmann FX-67K-1707150
Aspect ratio: 22.2
Empty weight: 249 kg (550 lb)
Max weight: 544 kg (1,200 lb)
Water ballast: 181 kg (400 lb)
Max wing loading: 53.7 kg/sq.m (11.0 lb/sq ft)
Max speed: 180 kt (334 km/h)
Stalling speed: 34 kt (63 km/h)
Min sinking at 43.5 kt (80 km/h): 0.52 m (1.71 ft) /sec

Apollo Fox

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The Apollo Fox is built according to the BCAR Section S constuction norm.
The aircraft has welded steel alloy tube fuselage covered with ceconite fabric. The wings are made of aluminium alloy both spars and ribs and then covered with ceconite.
Wing can be folded backwards. One pilot can do it within 10 minutes. The landing gears are aluminium plate sheet as year suspension. Wheels are equipped with hidraulic disc or mechanical drum brakes.
Available tail or nose wheel configurations.
Engine opts:
Rotax 582 UL Mod 99 (65Hp)
Rotax 912UL (80 Hp)
Rotax 912 ULS (100 Hp)
Jabiru 2200 (80Hp)
Subaru EA 81 (100 Hp).
Stall: 35 kt / 40 mph / 64 kmh
Cruise: 81 kt / 93 mph / 150 kmh
VNE: 97 kt / 112 mph / 180 kmh
Empty Weight: 274 kg / 604 lbs
MTOW Weight: 450 kg / 992 lbs
Take-off distance (50ft obstacle): 460 ft / 140 m
Landing distance (50ft obstacle): 660 ft / 200 m

Apis

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Apris 2

The Apis series includes both a 13- and 15-meter sailplane, is a combination of composite construction and old world craftsmanship. The Apis is intended for the sport flyer, but still holds several world records. They offer a forward-hinged canopy, automatic control hookups, in-flight adjustable rudder pedals, full-span flaperons, blended winglets, and Schempp-Hirth type airbrakes. They also make the Apis M, a 15-meter motorglider.

The Apis 2 is built with CFRP technology with 15 m span and T-tail. The wings are a multi trapezoid with raising tips. Aileron and flaps are interconnected (flaperons) and standard SH airbrakes give short landing approaches.
The spars are connected with two bolts in tongue/tongue technique. Rigging is straight forward and can be easily accomplished by one person. The glider fits in a standard sailplane trailer. The large canopy opens to the side and allows easy access to the ergonomic and roomy cockpit.
The Apis 2 includes a parachute rescue system. Wearing a pilots parachute is therefore not necessary and allows tall pilots to fit in the Apis 2.
The Apis 2 has a large canopy that opens to the side. The back-board can be adjusted continuously, the rudder pedals have some detents, and both can be readjusted during flight. The electric starter button and the throttle are located in the arm rest on the left side. The panel offers space for six instruments with 57 mm diameter in addition to the ECU indicator. One of these six can be replaced by a 80-mm-instrument alternatively. The battery fits into the quick-release rack in the fuselages nose. It energises both the ECU and the instruments.
The Apis 2 cockpit is made up of a double hull. The lightweight hollow section frame of the canopy offers a maximum stiffness in this area.
The Apis 2 takes off under its own power as a self launch glider. Despite the fixed tailwheel it is easy to control on the ground. Two aerodynamic tip wheels help eliminate the need for a wing runner.
The Apis 2 has a fixed gear with a wheel brake on the 4″ wheel.
After a short roll only climb rate is about 2.5 m/s (4.8 kt) at a speed of 80 to 85 km/h (45 kt). After about 150 m (500 ft) it will be airborne and it takes about 290 m (950 ft) over the 50 ft obstacle.
There is almost no trim change flying under engine or in gliding mode or while extending or retracting the engine. The camber changing flaps with a neutral trim will give you a speed range of 80 km/h (43 kt) at +9° to 160 km/h (86 kt) at -6°.
Thermal speed is about 80 km/h (43 kt) and minimum sink is 0.6 m/s (115 fpm). Best glide speed is 95 km/h (52 kt) which will give you a L/D of 39. Landing approach is at 90 km/h (48 kt) with positive flaps. The highly efficient airbrakes allow safe and steep approaches into short airfields. The Apis 2 can be landed with retracted or with extended engine.
The Apis 2 powerplant is an aircooled single cylinder Hirth F33 with intake and exhaust silencer. It generates 27 hp from 303 cc. The 148 cm ground adjustable carbon fibre propeller has been developed by Martin Wezel specially for the Apis 2. The noise level of the Apis 2 is at 57.7 db(A).
The powerplant is retractable. The process is controlled by ECU (Engine Control Unit) an instrument by TL elektronic. The extension of the powerplant is started by switching on the main switch, then the ignition. The ECU then takes over the process and the pilot can start the engine with the starter button. It is not necessary to manually control fuel valve or a choke lever. The ECU is optimizing the engine according to the temperature. During the retraction procedure for the powerplant the ECU is activating the propeller stop as soon as the RPM allows. Then the ECU is controlling the full procedure until the engine is completely stowed away.
The whole process takes about 20 seconds.
German certification in the Ultralight category was issued on 4 September 2003.

Apis 2
Span: 15 m
Wing area: 12.4 sq.m
Aspect ratio: 18.2
Length overall: 6.5 m
Empty weight: from 210 kg
Max. gross weight: 320 kg
Max. load factor: +5.3 / -3.3 g
L/D: 39 at 95 km/h (52 kt)
Min. sink rate: 0.6 m/s at 80 km/h (43 kt)
Flap settings: +9°, +5°, 0°, -3°, -6°
Stall: 35 kt / 40 mph / 65 kmh
Cruise: 81 kt / 93 mph / 150 kmh
VNE: 200 km/h (108 kt)
Engine: Hirth F 33 B, 27 PS / 19.3 kW
Carburetor: Mikuni membrane carburetor
Drive: Poly-V-belt 1:2.5
Propeller: Wezel 2-blade CFRPØ 1.48 m
Fueltank: 14 liter
Fuel consumption while climbing: 9 l/h
Noise level: 57.7 dB(A)

Apis 15M
Cruise: 51 mph
Stall: 36 mph
Aspect Ratio: 17-1
L/D: 40:1
Min sink: 115 fpm
Empty weight: 327 lb
Gross weight: 661 lb
Length: 20.6 ft
Wing span: 49.2 ft
Wing area: 132 sq.ft
Cockpit width: 32 in
Landing gear: tailwheel
Seats: 1

Apis M
Cruise: 56 mph
Stall: 36 mph
Aspect Ratio: 17-1
L/D: 40:1
Min sink: 115 fpm
Engine: Rotax 447, 40 hp
Fuel cap: 3.5 USG
Empty weight: 445 lb
Gross weight: 710 lb
Length: 20.6 ft
Wing span: 49.2 ft
Wing area: 132 sq.ft
Cockpit width: 32 in
Landing gear: tailwheel
Seats: 1

Apis Electric Self-Launch
Cruise: 51 mph
Stall: 36 mph
Aspect Ratio: 18.35-1
L/D: 40:1
Min sink: 108 fpm
Engine: Brushless DC, 13 kW
Empty weight: 452 lb
Gross weight: 710 lb
Length: 20.6 ft
Wing span: 49.2 ft
Wing area: 132 sq.ft
Cockpit width: 32 in
Landing gear: tailwheel
Seats: 1

APEV Pouchel / Pouchelec / Scoutchel

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Pouchel Classic

The original design, the Pouchel, was based upon the 1930s Henri Mignet-designed Mignet Pou-du-Ciel (Flying Flea), but constructed using three commercial household aluminium ladders to save construction time, cost and weight. The aircraft first flew on 14 March 1999 and 120 sets of plans were quickly sold.

When the ladder manufacturer no longer wanted to sell ladders for aircraft construction, due to liability concerns, Dalby redesigned the aircraft to use aeronautical rectangular aluminium tubing instead, which resulted in a lighter and cheaper aircraft, the Pouchel II.

Pouchel II

The Pouchel II replaced the original APEV Pouchel in production. The original Pouchel was constructed using three commercially available aluminium ladders, hence APEV is the Association pour la Promotion des Echelles Volantes, or in English, Association for the Promotion of Flying Ladders. Later the ladder manufacturer grew concerned about liability and refused to supply any more ladders. The Pouchel was then re-designed to use aeronautical rectangular aluminium tubing in place of the original ladders and the new aircraft was designated the Pouchel II. The Pouchel series are all derivatives of the classic 1930s Henri Mignet-designed Mignet Pou-du-Ciel (Flying Flea).

The Pouchel II features a cantilever rear wing with a strut-braced parasol front wing, a single-seat open cockpit without a windshield, fixed conventional landing gear and a single engine in tractor configuration. The aircraft is made from bolted-together aluminium tubing, with its flying surfaces covered in Dacron sailcloth. Its 6 m (19.7 ft) span front wing and 4 m (13.1 ft) span rear have a combined area of 12 m2 (130 sq ft) and both employ NACA 23112 airfoils. The prototype used a 40 hp (30 kW) Rotax 447 two-stroke powerplant, but the 35 hp (26 kW) Rotax 377 is also recommended. The 28 hp (21 kW) Hirth F-33 has also been fitted.

The Pouchel II sold for €4,000 in 2003. The APEV Pouchel II was supplied as plans or as a kit for amateur construction, but is no longer available. It has been replaced in production by the APEV Pouchel Light.

The Pouchel II was further refined into the Pouchel Light and an electric powered version, the Pouchelec.

Supplied as plans or as a kit for amateur construction, the Pouchel Classic is derived from the APEV Pouchel and features a cantilever rear wing and a strut-braced front parasol wing, a single-seat open cockpit, fixed conventional landing gear and a single engine in tractor configuration.

The Pouchel Classic differs from the earlier Pouchel in that it has a newly designed wooden fuselage to replace the aluminum ladder and rectangular tube design of the Pouchel and the Pouchel II. The Pouchel Classic’s fuselage is also longer. Its 6 m (19.7 ft) span front wing and 4 m (13.1 ft) span rear wing have a combined area of 12 m2 (130 sq ft) and employ NACA 23112 airfoils. Flying surfaces are covered in Dacron sailcloth. Standard engines recommended are the 35 hp (26 kW) Rotax 377 or the 40 hp (30 kW) Rotax 447 two-stroke powerplants. The Pouchel Classic kit sold for €5,000 in 2011.

A gasoline powered Pouchel (foreground) and a Pouchelec (background)

Gallery

Pouchel
Seats: one

Pouchel II
Engine: 1 × Hirth F-33, 21 kW (28 hp)
Propeller: 2-bladed wooden
Upper wingspan: 6 m (19 ft 8 in)
Lower wingspan: 4 m (13 ft 1 in)
Wing area: 12 sq.m (130 sq ft)
Airfoil: NACA 23112
Empty weight: 150 kg (331 lb)
Gross weight: 275 kg (606 lb)
Fuel capacity: 12 litres (2.6 imp gal; 3.2 US gal)
Cruise speed: 90 km/h (56 mph; 49 kn)
Stall speed: 40 km/h (25 mph; 22 kn)
Never exceed speed: 120 km/h (75 mph; 65 kn)
g limits: +4/-2
Rate of climb: 2.5 m/s (490 ft/min)
Wing loading: 18.75 kg/m2 (3.84 lb/sq ft)
Crew: one

Pouchel Classic
Engine: 1 × Rotax 447, 30 kW (40 hp)
Upper wingspan: 6 m (19 ft 8 in)
Lower wingspan: 4 m (13 ft 1 in)
Wing area: 12 sq.m (130 sq ft) total
Airfoil: NACA 23112
Empty weight: 150 kg (331 lb)
Gross weight: 250 kg (551 lb)
Fuel capacity: 30 litres (6.6 imp gal; 7.9 US gal)
Cruise speed: 90 km/h (56 mph; 49 kn)
Stall speed: 40 km/h (25 mph; 22 kn)
Never exceed speed: 120 km/h (75 mph; 65 kn)
g limits: +4/-2
Rate of climb: 3 m/s (590 ft/min)
Wing loading: 20.8 kg/m2 (4.3 lb/sq ft)
Crew: one

Pouchel Light
Crew: one

Pouchelec
Engine: electric
Crew: one

Scoutchel
Crew: one

Anzani

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Société des Moteurs Anzani

Alessandro Anzani in 1906, on his Fan type-engined motorbike

Anzani was an engine manufacturer founded by the Italian Alessandro Anzani (1877–1956), which produced proprietary engines for aircraft, cars, boats, and motorcycles in factories in Britain, France and Italy.

From his native Italy, Anzani moved to France where he became involved in cycle racing. He moved on to motorcycles and designed and built a record breaking lightweight engine. In 1907, he set up a small workshop in Paris with three staff and while they were building his engines, he designed a hydrofoil powered by one of his engines and propellers. The original Anzani Moteurs d’Aviation was situated at 112 Boulevard de Courbevoie, Courbevoie, Paris.

He supplied one of his engines to Enrico Forlanini and developed it further into a three-cylinder, air-cooled, radial engine ideal for the new aeroplanes. One of the early engines, the 25 hp Anzani W-3 or Fan type, was supplied to Louis Blériot who used it on his successful crossing of the English Channel in 1909.

Demand for the engines continued to grow and the original Paris workshop was replaced by a new factory at Courbevoie, Paris, and one in London was also added as well as licensed production by other makers. Another factory at Monza, Italy was added in 1914.

In 1920, Anzani turned to motor racing and built a small car with one of his 750 cc two-cylinder engines, air-cooled of course, which won several competitions. They also made a 1098 cc cyclecar between 1923 and 1924, as used in the T.B. Sports cyclecar.

On his 50th birthday in 1927, Anzani decided to sell his factories in Paris and London, keeping only the Monza works for sentimental reasons, and managed by Natale Baccanti.

Antonov 181

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The Antonov An-181 (or product 181, Ukrainian: Виріб 181, Russian: изделие 181) project was terminated because of the lack of funds due to the collapse of the Soviet Union. An interesting feature of the plane is its unusual arc-shaped wing, a so-called Channel wing. The aircraft has two seats next to each other, a conventional fixed landing gear, a V-tailplane, and high-wing equipped with a channel wing in the area of the propellers. Power from the engine is delivered by means of drive shafts and deflection gearboxes to the two-blade propellers. The aircraft received the registration СССР-190101 and is exhibited in the State Museum of Aviation of Ukraine. Willard Ray Custer had previously built aeroplanes with the same wing concept in the USA.

Crew: 2 people
Length: 7,31 m
Wingspan: 7,3 m
Height: 2,5 m
Wing area: 7 m²
Normal take-off weight: 820 kg
Maximum take-off weight: 900 kg
Engine: AP LOM M-337A, 6 cylinders, 103 kW
Propeller diameter: 1.5 m
Maximum speed: 225 km / h
Practical range: 530 km
Service height: 4200 m
Starting distance: 70 m
Landing distance: 80 m