Ultimate Biplane Corp 10-200
Engine: Lycoming O-360, 200 hp
HP range: 200-230
Length: 17.4 ft
Wing span: 16 ft
Wing area: 96 sq.ft
Empty weight: 925 lb
Gross weight: 1350 lb
Fuel capacity: 22 USG
Cruise: 170 mph
Stall: 60 mph
Range: 580 sm
Rate of climb: 2000 fpm
Takeoff dist: 450 ft
Landing dist: 500 ft
Seats: 1
Landing gear: tailwheel
Ultimate Aerobatics Ltd.
Ultimate Aircraft Corp
Ultimate Biplane Corp
Canada
Put on to market in 1980s kits to modify Pitts Special aerobatic biplane to improve performance.
Ultimate Aircraft Corp was founded 1990 to market modified Pitts Special aerobatic biplane in plans, kits and assembled forms, plus series of aerobatic/competition biplanes as 10 Dash 100,10 Dash 200,10 Dash 300 single-seaters, and two-seat 20 Dash 300.
The Topulteam is basically like a Top Secret with the wing tips chopped off. Only one was built.
Wing area: 11.8 m²
Wing span: 10.8 m
Aspect ratio: 9.8
Minimum pilot weight: 50 kg
Maximum pilot weight: 80 kg
Nose angle: 127°
The Styl is a 2005 hang glider for advanced pilots. Xavier Verges designed the 2005 Laminar Orbiter (Intermediate wing) in collaboration with ULteam, as a derivative of the StyL. It is marketed by Icaro 2000 as the Orbiter, and by ULteam as the StyL+.
The Styl+ is also a 2005 hang glider for advanced pilots. The ULteam Styl+ has options and tuning which provide the Styl+ with a slight edge in performance over the Orbiter.
The Icaro 2000 Orbiter 2 for Intermediate pilots appeared in 2016.
Styl+ 13
Wing area: 13.7 m²
Wing span: 9.7 m
Aspect ratio: 6.9
Hang glider weight: 27 kg
Minimum pilot weight: 60 kg
Maximum pilot weight: 85 kg
Packed length: 5 m
Packed length short: 4 m
Number of battens: 20
Nose angle: 128°
Styl+ 14
Wing area: 14.6 m²
Wing span: 10.2 m
Aspect ratio: 7.1
Hang glider weight: 30 kg
Minimum pilot weight: 80 kg
Maximum pilot weight: 95 kg
Packed length: 5.2 m
Packed length short: 4 m
Number of battens: 22
Nose angle: 128°
Styl+ 15
Wing area: 15.2 m²
Wing span: 10.4 m
Aspect ratio: 7.1
Hang glider weight: 31 kg
Minimum pilot weight: 85 kg
Maximum pilot weight: 110 kg
Packed length: 5.4 m
Packed length short: 4 m
Number of battens: 22
Nose angle: 126°
Styl+ 16
Laminar Orbiter 14
Wing area: 14.45 m²
Wing span: 10.35 m
Aspect ratio: 7.4
Hang glider weight: 30 kg
Minimum pilot weight: 70 kg
Maximum pilot weight: 100 kg
Minimum speed: 31 km/h
Maximum speed: 90 km/h
Packed length: 5.2 m
Packed length short: 4 m
Number of battens: 22
Nose angle: 128°
69, rue des Ebavous
38660 La Terrasse
France
Hang glider manufacturer circa 2005
Single seat single engined high wing mono¬plane with conventional three axis control. Wing has swept back leading and trailing edges, and constant chord; no tail, canard wing. Pitch control by fully flying canard; yaw control by tip rudders; roll control by spoilers; control inputs through yoke for pitch/roll and pedals for yaw. Wing braced from above by kingpost and cables, from below by cables; wing profile; single surface. Undercar¬riage has three wheels in tricycle formation; suspension NC on nosewheel and glass fibre suspension on main wheels. Push right go-¬right nosewheel steering connected to yaw control. Brake on nosewheel. Aluminium tube framework, with pod. Engine mounted below wing driving pusher propeller. Rudders and canard are covered in Stits polyriber fabric.
The prototype having made its first flights at the end of the summer in 1982. The prototype used a KFM 107ER motor which gives, according to Ultavia Aircraft, 25 hp at 6300 rpm and is becoming optional on the production models, the standard version coming with a Cuyuna 430R; a 2/1 reduction drive system for the 430R is also optional for $300 extra. The Ultavia is fitted with a yoke, rather than a stick. Its spoilers can be used differentially to control roll and together to act as air brakes. This machine comes as standard with a glass fibre nose cone, fitted with a Lexan transparent windscreen. The accent is put by the manufacturer on rapid rigging and de rigging, with single ¬surface resin impregnated Dacron wings which can be rolled up around the spars and stored in a bag, like a Rogallo wing. A genuine 15 min rigging time is claimed.
The Ultavia will be available during the summer of 1983, as a kit requiring 30h assembly at a price of $4595 (with a Cuyuna 430D) or factory built for $5395. A KFM 107ER engine costs $640 extra; an instrument panel is also available.
Engine: Cuyuna 430R
Max power 30hp at 5500rpm
Propeller diameter and pitch 54 x 17 inch, 1.37 x 0.43 m
Belt reduction, ratio 2.0/1
Power per unit area 0.19 hp/sq.ft, 2.1 hp/sq.m
Fuel capacity 5.0 US gal, 4.2 Imp gal, 18.9 litre
Wing span 32.0ft, 9.75m
Constant chord 5.0 ft, 1.52 m
Main wing area 155 sq.ft, 14.4 sq.m
Main wing aspect ratio 6.6/1
Nosewheel diameter overall 11 inch, 28 cm
Main wheels diameter overall 11 inch, 28cm
Empty weight 230 lb, 104kg
Max take off weight 480 lb, 217kg
Payload 250 lb, 113kg
Max wing loading 3.09 lb/sq.ft, 15.1kg/sq.m
Max power loading 16.0lb/hp, 7.2kg/hp
Never exceed speed 55mph, 88kph
Stalling speed 24mph, 39 kph
Best glide ratio with power off 10/1
Take off distance 150 ft, 45 m
Service ceiling 13,000 ft, 4000 m
1983: P.O. Box 3316, Las Vegas Municipal Airport, Las Vegas, NV 87701, USA.
UL builder
UL520i
Displacement: 5200 cc / 317 cu.in
Cylinders: 6
Compression Ratio: 8 : 1
Torque: 425 Nm
Power: 180 hp @ 3200 rpm
Weight installed: ±108 kg
UL520iS
Displacement: 5200 cc / 317 cu.in
Cylinders: 6
Compression Ratio: 8.7 : 1
Torque: 465 Nm
Power: 200 hp @ 3200 rpm
Weight installed: ±108 kg
UL390i
Displacement: 3900 cc / 238 cu.in
Cylinders: 6
Compression Ratio: 8.16 : 1
Torque: 320 Nm
Power: 140 hp @ 3200 rpm
Weight installed: ±100 kg
UL390iS
Displacement: 3900 cc / 238 cu.in
Cylinders: 6
Compression Ratio: 9.1 : 1
Torque: 370 Nm
Power: 160 hp @ 3200 rpm
Weight installed: ±100 kg
The engines feature FADEC (full authority digital engine control) with multi-point electronic fuel injection, and dual electronic ignition (with variable timing), excellent power-to-weight ratio, and high fuel efficiency in a conventional configuration: Air-cooled, direct drive, horizontally opposed four-cylinder.
UL Power Engines have been developed specifically for use in light aircraft and are manufactured with fully electronic ignition and multi-point fuel injection (FADEC) system as standard equipment.
UL Power engines are manufactured in Europe.
UL350i
Capacity: 3503 cc / 214 cu.in
Bore: 105.6 mm / 4.157 in
Stroke: 100 mm / 3.937 in
Max Power: 118hp @ 3300 rpm
Max Torque: 305Nm / 225 ft.lb @ 2400 rpm
Installed Weight: 78.4 kg/172.8 lb
Compression Ratio: 8:1
Fuel: min 95 OCT / 87 MON
Cylinders: 4
Firing Order: 1 – 3 – 2 – 4
Configuration: Flat-4, direct propeller drive, air-cooled
Direction of Rotation: Clockwise – seen from cockpit
Oil capacity: 2.5 lt / 0.66 US gal
DC output: 30 Amp (+/- 15 Amp available above engine/fuel pump needs)
TBO: 1500h / 10y
UL350iF
Max Power: 90 kW (120 hp)
Capacity: 3503 cc
Configuration: Flat-4, direct propeller drive, air-cooled
UL350iS
Capacity: 3503 cc / 214 cu.in
Bore: 105.6 mm / 4.157 in
Stroke: 100 mm / 3.937 in
Max Power: 130 hp @ 3300 rpm
Max Torque: 320Nm / 236 ft.lb @ 2400 rpm
Installed Weight: 78.4 kg/172.8 lb
Compression Ratio: 8.7:1
Fuel: min 98 OCT / 89 MON
Cylinders: 4
Firing Order: 1 – 3 – 2 – 4
Configuration: Flat-4, direct propeller drive, air-cooled
Direction of Rotation: Clockwise – seen from cockpit
Oil capacity: 2.5 lt / 0.66 US gal
DC output: 30 Amp (+/- 15 Amp available above engine/fuel pump needs)
TBO: 1500h / 10y
