The Pinaire Ultra-Aire is an American ultralight aircraft that was designed and produced by Pinaire Engineering. The aircraft was supplied as a kit for amateur construction.[1][2]
| Ultra-Aire | |
|---|---|
| Role | Ultralight aircraft |
| National origin | United States |
| Manufacturer | Pinaire Engineering |
| Status | Production completed |
Design and development edit
The aircraft was designed to comply with the US FAR 103 Ultralight Vehicles rules, including the category's maximum empty weight of 254 lb (115 kg). The aircraft has a standard empty weight of 252 lb (114 kg). It features a cable-braced high-wing, canard elevator, a single-seat, open cockpit, tricycle landing gear and a single engine in pusher configuration.[1][2]
The aircraft is made from bolted-together aluminum tubing, with its flying surfaces covered in Dacron sailcloth. Its compact single-surface 26 ft (7.9 m) span wing is supported by cables attached to a simple tube kingpost. The pilot is accommodated on a suspended sling seat. The control system is two-axis with pitch controlled by a canard elevator attached to the side-stick. Roll and yaw are controlled by wing tip rudders also controlled by the side-stick. The landing gear features a steerable nose wheel, also controlled by the side-stick. The standard engine supplied with the kit was the Cuyuna UL II-02 twin cylinder, two-stroke powerplant of 35 hp (26 kW).[1][2]
The aircraft was carefully tested using sandbag loading to +6 and -4 g without failure. Reviewer Andre Cliche describes the design as "well engineered". The Ultra-Aire can be quickly dismantled for ground transportation or storage.[1]
Specifications (Ultra-Aire) edit
Data from Cliche and the Virtual Ultralight Museum[1][2]
General characteristics
- Crew: one
- Length: 14 ft 2 in (4.32 m)
- Wingspan: 26 ft (7.9 m)
- Height: 6 ft 11 in (2.11 m)
- Wing area: 130 sq ft (12 m2)
- Empty weight: 252 lb (114 kg)
- Gross weight: 552 lb (250 kg)
- Fuel capacity: 5 U.S. gallons (19 L; 4.2 imp gal)
- Powerplant: 1 × Cuyuna UL II-02 twin cylinder two-stroke, 35 hp (26 kW)
Performance
- Maximum speed: 63 mph (101 km/h, 55 kn)
- Cruise speed: 40 mph (64 km/h, 35 kn)
- Stall speed: 22 mph (35 km/h, 19 kn)
- g limits: +6/-7
- Maximum glide ratio: 8:1
- Rate of climb: 600 ft/min (3.0 m/s)
See also edit
Aircraft of comparable role, configuration, and era
