Sawyer Skyjacker II

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
National origin United States
Designer Ralph V. Sawyer
First flight 3 July 1975
Status Production completed (1974)
Produced 1974
Number built One

Design and development

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]

Specifications (Skyjacker II)

Data from Plane and Pilot[2]

General characteristics

  • Crew: one
  • Capacity: one passenger
  • Length: 18 ft 0 in (5.49 m)
  • Wingspan: 18 ft 0 in (5.49 m)
  • Empty weight: 1,650 lb (748 kg)
  • Gross weight: 2,250 lb (1,021 kg)
  • Fuel capacity: 50 U.S. gallons (190 L; 42 imp gal)
  • Powerplant: 1 × Lycoming IO-360-A1B6D four cylinder, air-cooled, fuel-injected, four stroke aircraft engine, 200 hp (150 kW)

Performance

  • Maximum speed: 130 mph (210 km/h, 110 kn)
  • Cruise speed: 105 mph (169 km/h, 91 kn)
  • Stall speed: 45 mph (72 km/h, 39 kn)
  • Range: 525 mi (845 km, 456 nmi)
  • Rate of climb: 400 ft/min (2.0 m/s)

References
  1. "American airplanes: Sa - Si". aerofiles.com. Retrieved 10 June 2022.
  2. Plane and Pilot: 1978 Aircraft Directory, page 152. Werner & Werner Corp, Santa Monica CA, 1977. ISBN 0-918312-00-0
  3. Aerofiles (n.d.). "American airplanes: Sa - Si". Retrieved 18 October 2013.
  4. Federal Aviation Administration (18 October 2013). "N-Number Inquiry Results - N7317". Retrieved 18 October 2013.
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