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 181NaN1 span wing and is powered by a 2000NaN0 Lycoming IO-360-A1B6D engine. The aircraft has an empty weight of 1650lb and a gross weight of 2250lb, giving a useful load of 600lb. With full fuel of the payload is 300lb.[3]
The aircraft proved to be stall and spin proof. Its standard day, sea level take off run is 12000NaN0 and landing roll is 10000NaN0.
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]