Developed from the SL-90 Leshiy (first flown 1991) two-seat lightplane (first flown 1992) for pleasure flying and various other roles including training, survey, and agriculture.
Cruise: 81 kt / 93 mph / 150 kmh
VNE: 135 kt / 155 mph / 250 kmh
MTOW Weight: 840 kg / 1852 lbs
Take-off distance (50ft obstacle): 920 ft / 280 m
Landing distance (50ft obstacle): 720 ft / 220 m
Inteco produced the VM-23 Variant as a four-seat cabin monoplane.
The Technological Research Institute constituted the technical base on which Companhia Aeronáutica Paulista emerged. It was the Paulistinha project, passed on to Companhia Aeronáutica Paulista (CPA) together with the Planalto plane that generated the first royalties paid to the IPT.
The IPT-4 was designed by Clay Presgrave do Amaral of Instituto de Pesquisas Tecnológicas (IPT). The project had been initiated under the designation IPT-4 and although the design work had been contracted to CAP, IPT insisted on a wing profile of its own choosing that led to serious stability problems in the final product. It was a low-wing single-engine, for pilot training. The structure was made of wood, with plywood and canvas coverings. It was equipped with a 90-horsepower Franklin engine. The pilot and instructor in tandem open cockpits with fixed tailwheel undercarriage.
Clay do Amaral was part of the first board of the Companhia Aeronáutica Paulista, and IPT-4 became CAP-1, called Planalto.
First flying in June 1942 (prototype registration PP-TFW), successful test of the aircraft made it possible to sign a contract for the production of 20 aircraft. Since the institute did not have its own production facilities, the contract was handed over to Companhia Aeronautica Paulista (CAP). As a result, production aircraft were already produced under the designation CAP-1 Planalto.
The CAP-3 replaced the CAP-1’s Franklin 4AC engine with a de Havilland Gipsy with double its power in the mid-40s, but the stability problems remained unaddressed until CAP engineer Oswaldo Fadigas redesigned the wing in the CAP-6. The firm attempted to sell this latter type to the Ministry of Aeronautics, but succeeded only in selling conversion kits for the existing CAP-1s and -3s in the military’s inventory.
IPT-4 Planalto
Engine: Franklin 4AC-199-B3, 90 hp
Seats: 2
CAP-1
Engine: Franklin 4AC-199-B3, 67 kW (90 hp)
Wingspan: 8.6 m (28 ft 3 in)
Wing area: 12 sq.m (130 sq ft)
Aspect ratio: 6.16:1
Length: 6.4 m (21 ft 0 in)
Height: 2.6 m (8 ft 6 in)
Empty weight: 335 kg (739 lb)
Gross weight: 570 kg (1,257 lb)
Cruise speed: 155 km/h (96 mph, 84 kn)
Stall speed: 85 km/h (53 mph, 46 kn)
Endurance: 2.5 hours
Crew: 2
CAP-3
Engine: Gipsy
CAP-6
The IPT-3 glider, called Saracura, was a copy of the German Zoegling, intended for pilot training. The IPT-3 first flew in September 1942. It was a simple model, easy to handle.
Saracura = Saracura rail (Aramides saracura), bird from Latin America
The IPT-2 Aratinga was a glider produced by the Brazilian Instituto de Pesquisas Tecnologicas (IPT).
In the early 1940s, the Wood Research Department of the Instituto de Pesquisas Tecnologicas carried out intensive research into the use of indigenous woods in aircraft construction. The results were so promising that it was decided to set up its own aviation department. Its first director was Frede Abranches Brotero, who gathered a team of young engineers around him. Silvio de Oliveira was entrusted with the development of a new advanced glider and decided to revise the Grunau Baby, which was already used in Brazil.
The IPT-2 Aratinga was designed as a shoulder-wing aircraft with a conventional tail unit and a closed single-seat cockpit. A skid was under the hull. The machine was a wooden structure made from local woods, with the hull partly covered with plywood and partly covered with fabric. The wings were completely covered with fabric.
The only prototype IPT-2 Aratinga glider performed its maiden flight in July 1942.
The machine was later used by José Carlos de Barros Neiva, who developed it into a successful glider, the Neiva B Monitor.
Wing span: 10 m
Wing area: 8.7 m²
Length: 5.52 m
Empty weight: 185 kg
Minimum speed: 55 km / h
Top speed: 130 km / h
Seats: 1
In 1948, the Divison of Aeronautics of the IPT was created, originated from the Section of Aeronautics. The IPT designed a glider for primary instruction, the Gafanhoto, which was designated IPT-1 Gafanhoto (Grasshopper). A public-domain report was published by IPT containing the required information to build the glider.
To enable budding pilots to take their first steps, the Brazilian aero clubs needed a simple beginner glider. The IPT-1 Gafanhoto was the first aircraft designed by the newly established Instituto de Pesquisas Tecnologicas in São Paulo. The plan was to construct a simple plane that could be built from interested clubs themselves and could launch pulled by a winch or by a vehicle.
The gafanhoto was made entirely from local woods. The aircraft was a braced, braced high-wing aircraft. The fuselage, under which a single skid with rubber buffers was attached, consisted of a wooden frame and was clad with plywood. As with the SG 38 school glider, the pilot sat completely outdoors. The wings and the tail unit were a wooden structure covered with fabric. In the course of the flight tests it turned out that the wings had to be lowered, which led to the central struts being shortened by 20 cm.
First flown in 1942, the only machine built flew for several years, there was no series production.
Wing span: 10.35 m
Wing area: 15.3 m²
Length: 5.40 m
Empty weight: 115 kg
Max. Takeoff weight: 205 kg
Minimum speed: 55 km / h
Top speed: 120 km / h
Seats: 1
The Ministry of Defense and the High Command of Vietnamese Air Force assigned the Institute for Aviation Military Technology to manufacture the HL-1 trainer in January 1981.
The HL-1 was designed based on the Pilatus P3 of Switzerland, Zlin 526 of former Czechoslovakia and Yak 18 of the former USSR.
First flown in 1996.
The kit price for this twin pusher, including engines but not props or instruments, was US$23,500.
An auxilary 20 US Gallon fuel tank was optional.
Engine: 2 x Rotax 503, 53 hp
Top speed: 100 mph
Cruise: 90 mph
Stall: 40 mph
Rate of climb: 1200 fpm
Takeoff dist: 350 ft
Landing dist: 150 ft
Fuel capacity: 20 USG
Empty weight: 650 lb
Gross weight: 1400 lb
Height: 6.9 ft
Length: 19.4 ft
Wing span: 31.5 ft
Wing area: 155 sq.ft
Seats: 2
Landing gear: nose wheel
Island Aviation built a two-seat monoplane of braced parasol-wing configuration, known as the Inland Sport.
The Sky Arrow is based on the earlier, remotely piloted drones, the Rondine. The development of the proven airframe (with certification originally funded by the Italian government) into a series of sporting sircraft was undertaken, producing the Sky Arrow.
Guiseppe Archangeli made the first flight of the Sky Arrow from Ponzano, near Rome, on 13 July 1992. On that flight the prototype was fitted with the original metal wings, and it required only a 2 degree change in the tailplane incidence and minor mods to the controls.
To meet the civilian market demands and regulations, the Sky Arrow has been modified from the original concept, with the initial design studies being wind tunnel tested at the University. The original metal wings have been substituted with an all composite version.
The Sky Arrow 450T is a single-engine aircraft with vertically staggered tandem seats and dual controls. The instrument panel is located ahead of the front seat, and all the instruments are arranged to allow visibility from the rear seat, which is elevated somewhat in relation to the front seat. However, wing flaps, dual electronic switches and cabin heat can only be operated from the front seat. Operable from both seats are the brakes, trim, mixture control and carburettor air control.
The high wings are braced and rectangular in shape, and are made of a carbon-fibre sandwich with kevlar reinforcement, while the struts are constructed of alu¬minium and steel. The Sky Arrow 450 T wings are the as as the P92. The fuselage and empennage are made from carbon-fibre and kevlar. Landing gear is a fixed tricycle-type constructed of multilayered carbon-fibre and rubber shock absorbers for the nose gear. Load factor limits at a planned maximum all up weight of 450kg are +3.8G/-1.9G, with an ultimate strength of +7.6G/-3.8G before breakage occurs. The aeroplane is powered by an 80 hp four-stroke Rotax 912 engine, coupled by means of a reduction gear¬box with a ratio of 1:227 driving a two-bladed propeller.
The airframe is fully manufactured with composite materials (kevlar and carbon sandwich). The high-wing tandem configuration provides excellent visibility of over 300degrees. The Sky Arrow is fitted with either a Rotax 912 or 914 engine. The aircraft is offered to homebuilder enthusiasts as a kit which meets the FAA 49/51 percent rule. The Sky Arrow kit is composed of 10 subkits which can be bought separately and incrementally.
The Sky Arrow 450 and 650 are the same aircraft available as certified and ultralight versions. Easily converted to wheels, floats or amphibian, the 650TC is certified to JAR/VLA standard. Both the 450T ULM and 650T kit are built to that standard.
In 2014, the Sky Arrow 600 was manufactured by Italian maker Magnaghi. Base price 2014: $87,000 (Sky Arrow); $100,000 (loaded with SkyView 10-inch EFIS for limited time).
450T
Engine: Rotax 912, 80 hp.
Length: 7.6m (8.40ft)
Height: 2.56rn (8.40ft)
Wing span: 9.7rn (31.76 ft)
Wing area: 13.5sq.m (145.9sq.ft)
MTOW: 1450 lb / 450 kg
Wing loading at 450kg: 33kg/sq.m (8.221b/sq.ft).
Wing airfoil: Gottinga 398 modified.
Fuel capacity: 68 lt (l8gal.).
VNE: 121 kt.
Max. speed at sea level: 110 kt.
Cruise speed at sea level: 90 kt.
Stall speed: 33 kt.
Rate of climb: l000ft/min.
Take-off roll: 400ft.
Landing roll: 330ft.
Take-off over 50ft obstacle: 700ft.
Glide ratio at 60kt: 1:12.
Service ceiling: 15,000ft.
450T
Type: Production ultralight
Length: 7.60 m
Height: 2.6 m
Wingspan: 9.7 m
Wing area: 13.5 sq.m
Wing loading: 33.3 kg/sq.m
Engine: Rotax 912, 81 hp at 5800 rpm
Prop: 2 blade fixed pitch
Loading: +5.7 / -2.8
Empty weight: 290 kg
Useful load: 160 kg
MTOW: 450 kg
Vne: 121 kts
Max speed at SL: 108 kts
Cruise speed SL 75%: 90kts
Stall SL: 33 kts
ROC SL: 5.0 m/s
TO run: 90 m
Landing run: 90 m
Glide ratio: 13
Ceiling: 4000 m
Endurance 75% +30min: 4 hr 15 min
Max range 75% +30min: 380 nm
Sky Arrow Initiative indus. Sky Arrow 450T
Engine: Rotax 912, 80 hp
Wing span: 9.60 m
Wing area: 13.50 sq.m
MAUW: 500 kg
Empty weight: 320 kg
Fuel capacity: 68 lt
Max speed: 200 kph
Cruise speed: 175 kph
Minimum speed: 67 kph
Climb rate: 5 m/s
Max range: 700 km
Takeoff dist 450 kg: 110m
Takeoff dist 650 kg: 240m
Landing dist 450 kg: 90 m
Landing dist 650 kg: 135 m
Certification: VZ, VLA, PFA
Seats: 2
Fuel consumption: 13 lt/hr
Price (1998): 307 530 Fttc
Kit price (1998): 110 150 000 Lr
480T
Type: Production ultralight
Length: 7.60 m
Height: 2.6 m
Wingspan: 9.7 m
Wing area: 13.5 sq.m
Wing loading: 35.5 kg/sq.m
Engine: Rotax 912, 81 hp at 5800 rpm
Prop: 2 blade fixed pitch
Loading: +5.7 / -2.8
Empty weight: 303 kg
Useful load: 177 kg
MTOW: 480kg
Vne: 121 kts
Max speed at SL: 108 kts
Cruise speed SL 75%: 90kts
Stall SL: 34 kts
ROC SL: 4.8 m/s
TO run: 90 m
Landing run: 100 m
Glide ratio: 13
Ceiling: 4000 m
Endurance 75% +30min: 4 hr 15 min
Max range 75% +30min: 380 nm
500T
Type: Production ultralight
Length: 7.60 m
Height: 2.6 m
Wingspan: 9.7 m
Wing area: 13.5 sq.m
Wing loading: 3.7 kg/sq.m
Engine: Rotax 912, 81 hp at 5800 rpm
Prop: 2 blade fixed pitch
Loading: +5.7 / -2.8
Empty weight: 326 kg
Useful load: 174 kg
MTOW: 500 kg
Vne: 121 kts
Max speed at SL: 108 kts
Cruise speed SL 75%: 90kts
Stall SL: 35 kts
ROC SL: 4.5 m/s
TO run: 90 m
Landing run: 100 m
Glide ratio: 13
Ceiling: 4000 m
Endurance 75% +30min: 4 hr 15 min
Max range 75% +30min: 380 nm
650A/914 Exocet
Type: Homebuilt aircraft
Length: 7.60 m
Height: 2.8 m
Wingspan: 9.7 m
Wing area: 13.5 sq.m
Wing loading: 48.1 kg/sq.m
Engine: Rotax 914, 115 hp at 5800 rpm
Prop: 2 blade in flight adj
Loading: +5.7 / -2.8
Empty weight: 454 kg
Useful load: 196 kg
MTOW: 650 kg
Certification: EXP
Vne: 132 kts
Max speed at SL: 107 kts
Max speed at 15,000ft: 115 kts
Cruise speed SL 75%: 92 kts
Cruise speed 15,000ft 75%: 100 kts
Stall SL: 40 kts
ROC SL: 5.0 m/s
TO run: 180 m
Landing run: 135 m
Glide ratio: 10
Ceiling: 6000+ m
Endurance 75% +30min: 2 hr 15 min
Max range 75% +30min: 245 nm
650SP
Type: Homebuilt aircraft
Length: 7.60 m
Height: 2.8 m
Wingspan: 9.7 m
Wing area: 13.5 sq.m
Wing loading: 48.1 kg/sq.m
Engine: Rotax 912, 81 hp at 5800 rpm
Prop: 2 blade fixed pitch
Loading: +5.7 / -2.8
Empty weight: 400 kg
Useful load: 250 kg
MTOW: 650 kg
Certification: EXP
Vne: 132 kts
Max speed at SL: 90 kts
Cruise speed SL 75%: 80kts
Stall SL: 40 kts
ROC SL: 3.6 m/s
TO run: 275 m
Landing run: 75 m
Glide ratio: 10
Ceiling: 3000 m
Endurance 75% +30min: 4 hr 15 min
Max range 75% +30min: 340 nm
650T
Type: Homebuilt aircraft
Length: 7.60 m
Height: 2.6 m
Wingspan: 9.7 m
Wing area: 13.5 sq.m
Wing loading: 48.1 kg/sq.m
Engine: Rotax 912, 81 hp at 5800 rpm
Prop: 2 blade fixed pitch
Loading: +5.7 / -2.8
Empty weight: 350 kg
Useful load: 300 kg
MTOW: 650 kg
Certification: EXP
Vne: 132 kts
Max speed at SL: 107 kts
Cruise speed SL 75%: 90kts
Stall SL: 40 kts
ROC SL: 4 m/s
TO run: 240 m
Landing run: 135 m
Glide ratio: 12
Ceiling: 4000 m
Endurance 75% +30min: 4 hr 15 min
Max range 75% +30min: 380 nm
650T/914
Type: Homebuilt aircraft
Length: 7.60 m
Height: 2.6 m
Wingspan: 9.7 m
Wing area: 13.5 sq.m
Wing loading: 48.1 kg/sq.m
Engine: Rotax 914, 115 hp at 5800 rpm
Prop: 2 blade in flight adj
Loading: +5.7 / -2.8
Empty weight: 368 kg
Useful load: 282 kg
MTOW: 650 kg
Certification: EXP
Vne: 132 kts
Max speed at SL: 120 kts
Max speed at 15,000ft: 125 kts
Cruise speed SL 75%: 108 kts
Cruise speed 15,000ft 75%: 112 kts
Stall SL: 40 kts
ROC SL: 5.5 m/s
TO run: 150 m
Landing run: 135 m
Glide ratio: 12
Ceiling: 6000+ m
Endurance 75% +30min: 2 hr 15 min
Max range 75% +30min: 270 nm
650TC
Type: Production VLA
Length: 7.60 m
Height: 2.6 m
Wingspan: 9.7 m
Wing area: 13.5 sq.m
Wing loading: 48.1 kg/sq.m
Engine: Rotax 912, 81 hp at 5800 rpm
Prop: 2 blade fixed pitch
Loading: +5.7 / -2.8
Empty weight: 350 kg
Useful load: 300 kg
MTOW: 650 kg
Certification: JAR/VLA
Vne: 131 kts
Max speed at SL: 107 kts
Cruise speed SL 75%: 90kts
Stall SL: 40 kts
ROC SL: 4 m/s
TO run: 240 m
Landing run: 135 m
Glide ratio: 12
Ceiling: 4000 m
Endurance 75% +30min: 4 hr 15 min
Max range 75% +30min: 380 nm
1450A
Engine: Rotax 912, 79 hp.
HP range: 79-115.
Height: 8.7 ft.
Length: 24.93 ft.
Wing span: 31.49 ft.
Wing area: 114.6 sq.ft.
Weight empty: 900 lbs.
Gross: 1450 lbs.
Fuel cap: 19 USG.
Speed max: 109 mph.
Cruise: 93 mph.
Range: 440 sm.
Stall: 46 mph.
ROC: 600 fpm.
Take-off dist: 1800 ft (water).
Landing dist: 1800 ft (water).
Service ceiling: 13,000 ft.
Seats: 2.
Landing gear: floats & wheels.
1450A
Engine: Rotax 914, 100 hp
HP range: 100-115
Top speed: 136 mph
Cruise: 105 mph
Stall: 43 mph
Range: 360 sm
Rate of climb: 800 fpm
Takeoff dist water: 1200 ft
Landing dist water: 1200 ft
Service ceiling: 25,000 ft
Fuel capacity: 19 USG
Empty weight: 900 lb
Gross weight: 1450 lb
Height: 9.6 ft
Length: 24.9 ft
Wing span: 31.5 ft
Wing area: 144.6 sq.ft
Seats: 2
Landing gear: floats
1450L
Speed max: 118 mph.
Cruise: 105 mph.
Range: 497 sm.
Stall: 43 mph.
ROC: 800 fpm.
Take-off dist: 1300 ft.
Landing dist: 1100 ft.
Service ceiling: 13,000 ft.
Engine: Rotax 912, 79 hp.
HP range: 79-115.
Fuel cap: 19 USG.
Weight empty: 767 lbs.
Gross: 1450 lbs.
Height: 8.4 ft.
Length: 29.93 ft.
Wing span: 31.49 ft.
Wing area: 144.6 sq.ft.
Seats: 2.
Landing gear: nose wheel.
Sky Arrow Exocet
Engine: Rotax 914, 115 hp
Length: 24.9 ft
Height: 8.66 ft
Wing span: 31.5 ft
Wing area: 144.61 sq.ft
Empty weight: 1065 lb
MTOW: 1450 lb
Useful load: 385 lb
Fuel capacity: 16 Imp.Gal
Wing loading: 10 lb/sq.ft
Power loading: 12.6 lb/hp
Service ceiling; 18,000 ft
Max range with res: 250 nm
Takeoff roll; 400 m
Landing roll: 450 m
Prop: 3 blade composite Airplast
All Aero 