Initial work on the VUT100 Cobra project began in 2001 with the maiden flight made in November 2004. October 2006 saw the maiden flight of the VUT100 SuperCobra.
The VUT 100 Cobra was designed to offer speed with cabin comfort and ergonomics, low cost of ownership and long range. Planned to be available in two versions differing by the power units: The VUT 100-120i is equipped with a Lycoming IO-360-A1B6 (200HP) and mt-propeller MTW-12. The VUT 100-131i is equipped with a Lycoming IO-580-B1A (315HP) and the mt-propeller MTV-9.
The VUT100 Cobra was designed to enable easy and fast access to the parts of the airframe which require inspections and maintenance and the number of nodes which require inspections and adjustment were minimized.
The development team designed the airframe from traditional duralumin using 3D design systems and optimized from the strength point of view by FEM methods.
VUT100-120i Engine: Lycoming IO-360-A1B6, 200 hp Propeller: Hartzell HC-F3YR-1RF Diameter: 74 in / 188 cm Type: 3 blade, constant speed Length: 26.3 ft / 8 m Wing span: 33.5 ft / 10.2 m Internal cabin length: 122 in / 3.1 m Seats: 4 Internal cabin width: 51.5 in / 1.31 m Fuel usable: 90 USG / 340 lt Internal cabin height: 48 in / 1.22 m Max. take-off: 2,930 lb / 1,330 kg Useful load: 1,105 lb / 500 kg Max. level speed: 155 kts / 287 km/h Max. rate of climb: 1,000 fpm / 5 m/s Stall speed: 50 kts / 93 kph Range: 1,080 nm / 2,000 km Endurance: 8 hrs Load factors: +3.8g -1.52g (Normal category) / +4.4g -1.76g (Utility category)
VUT100-131i Engine: Lycoming IO-580-B1A, 315 hp Propeller: Hartzell HC-F3YR-1RF Diameter: 76 in / 193 cm Type: 3 blade, constant speed Length: 26.3 ft / 8 m Wing span: 33.5 ft / 10.2 m Internal cabin length: 122 in / 3.1 m Seats: 4 Internal cabin width: 51.5 in / 1.31 m Fuel usable: 90 USG / 340 lt Internal cabin height: 48 in / 1.22 m Max. take-off: 3,200 lb / 1,450 kg Useful load: 1,260 lb / 570 kg Max. level speed: 175 kts / 324 km/h Max. rate of climb: 1,000 fpm / 5 m/s Stall speed: 55 kts / 103 km Range: 1,000 nm / 1,830 km Endurance: 6 hrs Load factors: +3.8g -1.52g (Normal category) / +4.4g -1.76g (Utility category)
In 1996 Aerotechnik with Evektor began development of the EV-97 team Eurostar airplane.
A two-seat light or ultralight monoplane designed for sport/leisure flying, touring and training with limitation to non-aerobatic VFR operations. The Eurostar is aerodynamically controlled, single-engine, two-seat, low-wing, all metal plane with a fixed tricycle undercarriage and controllable nose wheel. The aircraft is equipped with four cylinder four stroke 80 HP Rotax 912 UL engine, optionally 100 HP Rotax 912 ULS or 80 HP Jabiru 2200.
Beginning in 2000 was the development of the EV-97 VLA airplane. This aircraft is called SportStar in US and EuroStar in Europe. Development of the SportStar version began in 2003.
By 2009, over 800 of the EuroStar had been delivered worldwide and the 2009 price was 50000 Euro.
Eurostar SL
The EuroStar SL is an advanced ultralight airplane with 46.5 inches / 1.18 meters of shoulder room, new system of cockpit climate control, and state of the art glass cockpit avionics. During testing more than 450 spins in all configurations were carried out. The airplane was type approved by the Ministry of Defence of the Czech Republic and is operated by the Pilot Training Centre of the Czech Army for initial pilot training. The EuroStar SL has an all metal anodised and corrosion-proofed aluminium airframe. It has all joints of construction riveted as well as bonded for durability and long fatigue life. The EuroStar is certified for towing of the sailplanes up to 700 kilos (Duo Discus, Janus, Ventus, ASK 21, Ventus, Blanik etc.) and for towing of banners up to 140 sq.m.
SportStar Max
The SportStar MAX is an S-SLA aircraft business travel or training. The airplane was the very first aircraft approved by the FAA (2005) in the U.S. S-LSA category and is holder of the prestigious “S-LSA Aircraft of the Year” honour from AeroNews Network (ANN). The SportStar MAX with a re-designed, based on an EASA JAR-VLA certified pilot training airplane, airframe at 1320 lb / 600 kg MTOW provides up to 640 lb / 290 kg of useful load combined with range 700 nm / 1300 km, and was available as an IFR version. The SportStar MAX combines aerodynamic composite materials with an all-metal primary airframe structure. The SportStar MAX build quality and reliability is based on Evektor´s certified aircraft production by the European Aviation Safety Agency (EASA), ISO 9001:2000 Quality Management System as well as LAMA certification. The canopy gives 46.5 inches / 1.18 meters of shoulder room, and glass cockpit avionics. The SportStar MAX has an all metal anodised and corrosion-proofed aluminium airframe with all joints of construction riveted as well as bonded. The SportStar is certified for towing of the sailplanes up to 700 kilos (Duo Discus, Janus, Ventus, ASK 21, Ventus, Blanik etc.) and for towing of banners up to 140 sq.m. The SportStar is a Light Sport Aircraft (LSA) designed for pilot training, sport and leisure flying and touring with limitation to non-aerobatic VFR operations.
The Evektor fully certified (European EASA standard), general aviation-quality aircraft is conventionally powered (Rotax), and has evolved to the flagship Harmony and includes the SportStar MAX, both with all-metal construction, long range economy cruise at 110 knots by 2012. Base prices 2012: US$98,000 (MAX); US$102,000 (Harmony).
Evektor EV-97 Team Eurostar Engine: Rotax 912 ULS, 100 hp TBO: 1,500 hrs Propeller: Fixed, on-ground or in-flight adjust Cabin width: 46.5 in / 1.18 m Length: 17 ft 7.5 in / 5.98 m Height: 8 ft 1.6 in / 2.48 m Wing span: 26 ft 7 in / 8.1 m Empty weight: 609 lb / 276 kg MTOW: 992 lb / 450 kg Design load: +6 g / -3g Max. baggage: 33 lb / 15 kg Wing tanks cap: 17.17 USG / 65 lt Vne: 270 km/h Stall speed: 65 km/h Maximum level speed: 240 km/h Rate of climb: 7.5 m/s Cruise 75% power: 200 km/h Service ceiling: 6,000 m Take-off distance: 200 m Maximum range: 750 km Landing distance: 300 m
Engine: Rotax 912 UL, 80 hp TBO: 1,500 hrs Propeller: Fixed, on-ground or in-flight adjustable Cabin width: 46.5 in / 1.18 m Length: 17 ft 7.5 in / 5.98 m Height: 8 ft 1.6 in / 2.48 m Wing span: 26 ft 7 in / 8.1 m Empty weight: 609 lb / 276 kg MTOW: 992 lb / 450 kg Design load: +6 g / -3g Max. baggage: 33 lb / 15 kg Wing tanks cap: 17.17 USG / 65 lt Vne: 270 km/h Stall speed: 65 km/h Maximum level speed: 220 km/h Rate of climb: 5.0 m/s Cruise 75% power: 180 km/h Service ceiling: 6,000 m Take-off distance: 280 m Maximum range: 750 km Landing distance: 300 m Glide Ratio: 1:12
Evektor SportStar Engine: Rotax 912ULS, 100 hp TBO: 1500 hr Prop: Fixed, ground adjustable Wingspan: 28 ft 5 in / 8.65 m Overall length: 19 ft 7.5 in / 5.98 m Height: 8 ft 2 in / 2.48 m Power loading: 12.1 lb/hp Max ramp weight: 1212 lb Gross weight: 1212 lb MTOW US VG: 1,320 lb / 600 kg Landing weight: 1212 lb Empty weight, std: 680 lb / 309 kg Useful load: 522-640 lb /237-291 kg Useful fuel, std: 31.2 USG / 118 lt Payload, full std. fuel: 355 lb Seating: 2 Cabin width: 46.5 in / 1.18 m Vne: 146 KIAS / 270 km/h Maximum level speed: 115 KCAS / 213 km/h Cruise 75% pwr: 100-110 kt Fuel consumption 75%: 4.5-5.0 USG/hr Stall speed: 40-46 kt / 74-83 kph Best rate of climb SL: 840 fpm Service ceiling: 13,100 ft Takeoff ground roll: 620 ft / 190 m Landing ground roll: 590 ft / 180 m Baggage volume: 6.2 cu.ft / 175 lt Max. baggage: 55 lb /25 kg Design load: +6 g / -3g Maximum range: 700 nm / 1,300 km Total endurance: 8.5 hrs
Designed by Karel Dlouhy in the middle of 70´s as a powered self-launching derivative of the LET L 13 Blanik, the Vivat uses a rear fuselage and wings very similar to the L 13. Of all metal with fabric covered control surfaces. The wings do not incorporate the flaps of the L 13, but retain the DFS type airbrakes. The center section and cockpit area are widened to make room for the two-place side- by-side seats. The main wheel is retractable, and the wingtip outrigger wheels fold back at the same time. The tail wheel is steerable, being linked to the rudder circuit. It can also be unlocked and be fully castoring outside the normal rudder-linked range. The Vivat was offered with a choice of engines, the SHE with the Czech Walter mikron, matched to a three position Hoffmann propeller, and the SL with a German Limbach fitted with a Muhlbauer electrically operated constant speed feathering propeller. The engine compartment is fitted with cooling shutters which can be closed to reduce drag when the engine is off. Both models were offered with a two wheel non-retractable landing gear as an alternative to the single retractable wheel with tip outriggers.
Around 200 units of the L-13 Vivat were successfully exported to USA, Canada, Australia, South Africa, Egypt, Israel, Germany, Sweden and many other countries. Production of the L13 Vivat motorgliders ended circa 2005.
M132A Cycle: supercharged 4 No cylinders: 4 inline Bore: 105 mm Stroke: 115 mm Compression: 6.3 Displacement: 3980 cc Cooling: Air Ignition: Double magneto Drive: Direct Weight: 105 kg Max pwr: 120 hp at 270 rpm Fuel consumption: 26 lt/hr
From the Matra-Cantinieau MC-101 / AC-11 Aerotecnica developed the AC-12 and AC-13, the former powered by a 150hp Lycoming O-320 engine and the latter by a Turbomeca Artouste I gas turbine.
A twin seat single-rotor helicopter, the AC-12 has a full all-metal monocoque fuselage with a large overhead ‘spine’ encompassing the boom and engine mounted above the cabin. Three-blade rotor with double-articulated blades. Each blade has a solid machined duralumin spar which forms the leading-edge, duralumin ribs and trailing-edge. Space between ribs is filled with a plastic foamed resin compound named Klogecell, with a final overall covering of Fiberglas. Floating hub, with cyclic and collective-pitch changes made through a “spider.” Rotor blade area each 0.71sq.m. Rotor disc area 57sq.m. Three-blade anti-torque rotor of similar construction to main rotor. Anti-torque rotor blade area 0.0927sq.m. Anti-torque rotor disc area 2.26sq.m.
The main rotor is driven direct from the engine gear-box (7.28 : 1 ratio) and clutch through a universal joint. The anti-torque rotor is driven through a gear-box (1.4 : 1 ratio) and cardan shaft.
Enclosed cabin seating two side-by-side with dual controls. Entrance door on each side of cabin. Landing gear is skid type. Track of skids 2.0m
Two prototypes were built with Spanish Government funding in Madrid by AISA, with a transmission and reduction gear designed on motor-car principles and built by the ENHASA airscrew company. One 168hp Lycoming O-360-B2A fan-cooled engine mounted above the cabin with direct drive through the gear-box to the main rotor. Fuel tank under seats with capacity of 60 litres. Oil capacity 9 litres. The first of these flew on July 20, 1956.
A production order for 12 was received from the Spanish Government with a military designation of XZ-1 where they served for a relatively short period before being retired.
Cantinieau moved on to a two-seater, the MC.101, which retained the general layout of the C.100 but with a much cleaned-up structure and a 105hp Hirth engine. Two examples of the MC.101 were built by Matra (F-WGIX and F-WGIY), the first of which was flown by Gerard Henry at Buc on 11 November 1952. It was shortly after this that Cantinieau gained the interest of the Marquis del Merito, a Spanish industrialist, who had established Aerotecnica SA as an aerial photography and crop spraying business based at Cuatro Vientos near Madrid. Aerotecnica S.A. began building helicopters by hiring French engineer Jean Cantinieau and acquiring the Matra-Cantinieau MC-101 light helicopter built by the French Societe Matra in 1952. This helicopter was given the designation AC-11 (Aerotecnica-Cantinieau-11). It became evident that the aircraft was underpowered in Madrid’s hot and high conditions and a 150hp Lycoming was installed – in which form it became the Model AC.12. From the AC-11 have been developed the AC-12 and AC-13.
Engine: 105 h.p. Hirth Rotor diameter: 26 ft. 4 in Rotors: 3-blade main; 3-blade tail Fuselage length: 22 ft Loaded weight: 1760 lb. Ceiling; 9,840 ft. Typical range: 250 miles at 96 m.p.h. with ful1 load. Seats: 2
Single seat single engined high wing mono¬plane with hybrid control. Wing has constant chord; cruciform tail. Pitch control by weight¬shift; yaw control by fully flying rudder; no separate roll control; control inputs through weight shift for pitch/yaw/roll. Wing braced from above by kingpost and cables, from below by cables; single ¬surface. Undercarriage has three wheels in tricycle formation; torsion bar suspension on all wheels. Nosewheel steering. No brakes. Aluminium tube framework, without pod. Engine mounted above wing driving pusher propeller. Framework from 6061T6 and 2024T3 aluminium, 4130 aircraft steel; coated stainless steel rigging, Dacron wing surface. The Canadian Skyrider is a hybrid control ultra¬light, the pilot using his swing seat as the principal means of control, with his weight shift aided in yaw by a rudder. Standard power unit is a twin cylinder Cuyuna 430R with dual ignition and in flight recoil restart facility. Alternatively, the sing¬le cylinder Cuyuna 215 cc engine may be fitted. Construction time is estimated at 30 h; a trailer is needed for transportation. After producing between 150 and 200 aircraft, the future of the company seemed in some doubt in 1983.
Engine: Cuyuna 430R, 30 hp Propeller: 48 x 23 inch, 1.22 x 0.58 m Reduction ratio: 2.0/1 Power per unit area: 0.19 hp/sq.ft, 2.0 hp/sq.m Wing span: 32.0ft, 9.75m Fuel capac¬ity: 3.8 USG, 3.2 ImpG, 14.4 lt Contant chord: 5.0 ft, 1.52 m Total wing area: 160 sq.ft, 14.9 sq.m Aspect ratio: 6.4/1 Nosewheel dia. Overall: 11 inch, 28cm Empty weight: 155 lb, 70 kg Main wheels dia overall: 11 inch, 28cm MTOW: 420 lb, 191 kg Payload: 265 lb, 120 kg Vne: 55 mph, 88 kph Wing loading: 2.62 lb/sq.ft, 12.8 kg/sq.m Power loading: 14.0 lb/hp, 6.4 kg/hp
Engine: Cuyuna 215R, 20 hp Power per unit area: 0.13 hp/ sq.ft, 1.3 hp/ sq.m Wing span 32.0ft, 9.75m. Fuel capac¬ity: 3.8 USG, 3.2 ImpG, 14.4 lt Contant chord: 5.0 ft, 1.52 m Total wing area: 160 sq.ft, 14.9 sq.m Aspect ratio: 6.4/1 Nosewheel dia overall: 11 inch, 28cm Vne: 55 mph, 88 kph Main wheels dia overall: 11 inch, 28cm
The Aerotec A-122 Uirapuru 2 seat Brazilian military trainer aircraft first flew on 2 June 1965, powered by a 108 hp Lycoming O-235-C1 engine. A second followed powered by a 150 hp Lycoming O-320-a and was offered to the Brazilian Air Force as a replacement for its locally built Fokker S.11 and S.12 basic trainers. Thirty Uirapurus were ordered for this purpose early in 1968 under the military designation T-23. 40 more were ordered in 1969. They have a 160 hp Lycoming O-320-B2B and differ from the civilian model in having fully-adjustable seats, stick controls, a nose wheel the same size as the mains, and a modified cockpit canopy in which only the centre portion slides rearward.
Following the loss of the first production T-23 in 1968, a small ventral fin was added to improve spin recovery.
They were used by Brazilian, Bolivian & Paraguayan Air Forces.
Engine: Lycoming: O-320-B2B, 160 hp Wingspan: 27 ft 10.75 in / 8.50 m Length: 21 ft 8 in / 6.60 m Empty weight: 1191 lb / 540 kg MTOW: 1825 lb / 840 kg Max cruise 5000ft / 1525m: 100 kt / 115 mph 185 kph Service ceiling: 14,760 ft / 4500m Max range: 700 nm / 805 mi / 1300 km Max endurance: 6 hr 30 min Seats: 2 Baggage capacity: 66 lb / 30 kg
The 1941 Culver Cadet was a 2-place low wing light plane powered by a 75hp Continental engine and capable of cruising at 120mph. After much design and analysis, Neal La France offers plans for a homebuilt version of the Cadet. The Cadet STF features a steel tube, fabric covered fuselage instead of the production wood fuselage. A considerable weight savings and double the strength was obtained with the new design. Prototype is powered by a 100 hp Continental engine.
Cadet STF Engine: Continental C-90, 90 hp. HP range: 85-125 Wing span: 27 ft. Wing area: 120 sq.ft. Length: 18.5 ft. Height: 5.5 ft. Weight empty: 790 lbs. Gross: 1305 lbs. Fuel cap: 25 USG. Speed max: 175 mph. Cruise: 130 mph. Range: 500 sm. Stall: 50 mph. ROC: 800 fpm. Take-off dist: 800 ft. Landing dist: 825 ft. Service ceiling: 17,500 ft. Seats: 2. Landing gear: retractable tail wheel.
Engine: Continental O-200, 100 hp Wing span: 8.23 m Wing area: 11 sq.m MAUW: 592 kg Empty weight: 403 kg Fuel capacity: 95 lt Max speed: 282 kph Cruise speed: 217 kph Minimum speed: 88 kph Climb rate: 5 m/s Seats: 2 Fuel consumption: 22 lt/hr Plan price (1998): $375
