The Sawyer Skyjacker II is an American homebuilt aircraft that was designed and produced by Ralph V. Sawyer of Lancaster, California, in 1974. It first flew on 3 July 1975.[1] The aircraft was intended as a research project and as such only one was built.[2]
| Skyjacker II | |
|---|---|
| Role | Experimental homebuilt aircraft Type of aircraft |
| National origin | United States |
| Designer | Ralph V. Sawyer |
| First flight | 3 July 1975 |
| Status | Production completed (1974) |
| Produced | 1974 |
| Number built | One |
The Skyjacker II was designed to explore ultra-low aspect ratio wing designs and in particular the stability, controllability and capability of the configuration. The design was intended to be easily scalable to much larger aircraft. It has no complex curves and was designed to be easy to construct. It features a cantilever mid-wing, a two-seats-in-tandem enclosed cockpit under a glazed canopy, fixed tricycle landing gear with wheel pants and a single engine in pusher configuration.[2]
The aircraft is made from sheet aluminum, has an 18.0 ft (5.5 m) span wing and is powered by a 200 hp (149 kW) Lycoming IO-360-A1B6D engine. The aircraft has an empty weight of 1,650 lb (750 kg) and a gross weight of 2,250 lb (1,020 kg), giving a useful load of 600 lb (270 kg). With full fuel of 50 U.S. gallons (190 L; 42 imp gal) the payload is 300 lb (140 kg).[2][3]
The aircraft proved to be stall and spin proof. Its standard day, sea level take off run is 1,200 ft (366 m) and landing roll is 1,000 ft (305 m).[2]
The sole example built was registered in the United States with the Federal Aviation Administration in 1974, but its registration was cancelled in August 2013.[4]
Data from Plane and Pilot[2]
General characteristics
Performance