LSA/UL

KAI Strekoza

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The Strekoza (Three axis) was a single seat single engined high wing mono¬plane with three axis control circa 1983. Constant chord wing; conventional tail. Pitch control by elevator on tail; yaw control by fin mounted rudder; roll control by full span ailerons. Engine mounted at wing height driving tractor propeller.
The Strekoza is a com¬pletely original design from the students at the polytechnic of Kuibychev and in concept of a mini aeroplane. Using a conventional tail supported by a metal framework, the Strekoza carries slotted ailerons along the entire trailing edge of its constant chord high wing. The engine, an air cooled Wichr 25 developing 25 hp, is placed in a nacelle on the leading edge of the wing, connected to a two blade 43 inch (1.10 m) propeller.

Length overall 19.9 ft, 6.07 m.
Wing span 23.6 ft, 7.20 m.
Constant chord 3.6 ft, 1.10 m.
Total wing area 105 sq.ft, 9.80 sq.m.
Engine: Wichr 25, 25 hp.
Propeller diameter: 43 in, 1.10m.
Power per unit area 0.24hp/ sq.ft, 2.6hp/sq.m
Empty weight 331 lb, 150 kg.
Max take off weight 507 lb, 230kg.
Payload 176 lb, 804.
Max wing loading 4.831b/sq.ft, 23.5kg/sq.m
Max power loading: 20.31b/hp, 9.2kg/hp.
Max level speed: 62mph, 100kph.
Landing speed 28mph, 45 kph.
Stalling speed 31 mph, 50 kph.
Take¬off distance 660 ft, 200 m.
Landing distance 590 ft, 180 m.

Kubíček M-2 Skaut

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In 2005 Petr Kubiček, encouraged by aerospace engineering students at Brno University, began to design a modernised Mráz M-2 Skaut with the hope of production. The first Kubicek M-2 Scout (the name was Anglicised) of the 21st century appeared, unflown, at Aero ’09 held in Friedrichshafen in the spring of 2009 and flew for the first time on 7 May 2009. The Scout design began with the original plans reassessed with modern methods and using a metal rather than wood structure, supplemented with some composite materials for the engines cowling and flying surface tips.

Externally the old and new aircraft are similar, wings and tail having the same features and the side-by-side seating retained. The aircraft is made from riveted and bonded aluminum sheet and is completely corrosion-treated after assembly. Electrically operated flaps are fitted to the Scout and there is a central trim tab on the elevator. Its fixed tricycle undercarriage is mounted on the fuselage with cantilever composite mainlegs. The mainwheels have brakes operated with a central lever and the nosewheel has helical springing. All wheels are spatted.

The new M-2 was designed to comply with the Fédération Aéronautique Internationale microlight rules and US light-sport aircraft rules.

After its first flight in May 2009, the Scout prototype appeared at several Czech airshows and fly-ins.

Two versions are being developed, one to meet the US Light Sport requirement with a maximum take-off weight (MTOW) of 598 kg (1,320 lb) and a second for the European Ultralight MTOW limit of 450 kg (992 lb). Both these MTOWs are less than that of the original Skaut and empty weight are also less. Certification was proceeding in 2010, with the aim of first deliveries during 2011.

M-2 Scout LSA
US light-sport category
Engine: Rotax 912ULS, 73.5 kW (98.6 hp)
Propeller: 3 blade ground adjustable
Wingspan: 9.6 m (31.5 ft)
Wing area: 12.4 m2 (133 sq ft)
Length: 6.87 m (22 ft 6 in)
Height: 2.35 m (7 ft 9 in)
Empty weight: 320 kg (705 lb)
Gross weight: 600 kg (1,323 lb)
Fuel capacity: 90 L (23.5 US gal; 19.8 Imp gal).
Maximum speed: 220 km/h (140 mph, 120 kn)
Cruise speed: 180 km/h (110 mph, 97 kn)
Stall speed: 72 km/h (45 mph, 39 kn) in the landing configuration
Never exceed speed: 260 km/h (160 mph, 140 kn)
ROC: 6.0 m/s / 1.181 ft/min
Endurance: 6 hours
g limits: +4/-2
Crew: one
Capacity: one passenger
Cockpit width: 120 cm (47 in)

M-2 Scout UL
European ultralight category
Engine: Rotax 912ULS, 73.5 kW (98.6 hp)
Propeller: 3 blade ground adjustable
Wingspan: 9.6 m (31.5 ft)
Wing area: 12.4 m2 (133 sq ft)
Length: 6.87 m (22 ft 6 in)
Height: 2.35 m (7 ft 9 in)
Empty weight: 320 kg (705 lb)
Gross weight: 472.5 kg (1,042 lb)
Fuel capacity: 90 L (23.5 US gal; 19.8 Imp gal).
ROC: 5.0 m/s (984 ft/min)
Cockpit width: 120 cm (47 in)
Crew: one
Capacity: one passenger

K & S Jungster I

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The Jungster I was developed as an 8/10 scale version of the famous Bunker Jungsmeister aerobatic airplane. The intention was to capture many of the flying qualities of the Jungmeister in a smaller size. This all-wood, fabric-covered biplane has a swept-back wing design of about 11 degrees to keep the center of lift close to the center of gravi¬ty. It can handle engines rated from 85 to 150 hp and is a frisky single place aerobatic plane.

Gross Wt, 1000 lb
Empty Wt. 605 lb
Fuel capacity 16 USG
Wingspan 16’5”.
Length 16’.
Wing area: 80 sq.ft.
Top 200 mph.
Cruise 150 mph
Stall 52 mph
Climb rate 2500+ fpm
Takeoff run 300 ft
Landing roll 800 ft
Range 300 miles
Seats: 1.

Kraft Super Fli

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Designer Phil Kraft is a world champion model-builder, and he used his know-how to construct the Super Fli N5PK with assistance by Paul White. This unlimited aerobatic low-¬winger has seating for one under a transparent canopy. Fuselage construction is a steel-tube frame covered by aluminum, while the wings are a spruce and plywood structure covered with plywood.

The K-1 Super-Fli first flew in December 1974 under the power of a 200hp Lycoming AIO-360-A1D engine.

Although the K-1 was made available for amateur construction, no addition aircraft were completed. It is possible that a later owner (Ian Paden) installed a more powerful IO-540 engine.

The N5PK registration for the aircraft was cancelled in March 1990.

Gross Wt. 1450 lb.
Empty Wt. 1060 lb.
Fuel capacity 23 USG.
Wingspan 24’6”.
Length 20’.
Engine 200-hp Lycoming.
Top mph 185.
Cruise mph 135.
Stall mph 48.
Climb rate 1800 fpm.
Ceiling 12,000 ft
Takeoff run 800 ft.
Landing roll 1000 ft.
Range 400 miles.