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The Sawyer Skyjacker II is an American homebuilt aircraft that was designed and produced by Ralph V. Sawyer of Lancaster, California, in 1974. The aircraft was intended as a research project and as such only one was built.〔Plane and Pilot: ''1978 Aircraft Directory'', page 152. Werner & Werner Corp, Santa Monica CA, 1977. ISBN 0-918312-00-0〕 ==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.〔 The aircraft is made from sheet aluminum, has an span wing and is powered by a Lycoming IO-360-A1B6D engine. The aircraft has an empty weight of and a gross weight of , giving a useful load of . With full fuel of the payload is .〔 The aircraft proved to be stall and spin proof. Its standard day, sea level take off run is and landing roll is .〔 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. 抄文引用元・出典: フリー百科事典『 ウィキペディア（Wikipedia）』 ■ウィキペディアで「Sawyer Skyjacker II」の詳細全文を読む スポンサード リンク
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