Origins and research goals Ralph V. Sawyer initiated the Skyjacker II as a personal research project to investigate ultra-low aspect ratio wings (approximately 1:1, near-square planform) for superior low-speed stability, short takeoff and landing (STOL) performance, and inherent safety without traditional tails or rudders. Influenced by 1970s experimental aviation trends and his NASA lifting-body experience, Sawyer hypothesized that such wings could generate vortex lift for benign stall behavior ("mushing" descent instead of abrupt drop) and eliminate spin risks. The design emphasized simplicity—no compound curves, highly stressed components, or complex controls—to enable easy, low-cost construction and scalability to larger aircraft. Development began with subscale models: a 12-inch cardboard glider and a six-foot radio-controlled twin-engine version that flew "extremely fast and well." A proposed larger variant (36-foot span, twin turboprops, four seats) was started but abandoned.
Construction and initial testing Built at Mojave Airport by Sawyer and business partner Mike Carmack, the all-metal prototype (N7317) featured straightforward sheet aluminum fabrication. It used a
Lycoming IO-360-A1B6D pusher engine, initially with a two-blade propeller later upgraded to a three-blade constant-speed unit for slight thrust improvement. Ground tests confirmed structural integrity before the maiden flight on July 3, 1975. Limited flights (only by Sawyer and Carmack) validated low-speed handling but showed marginal climb (≈250 ft/min observed in some tests, though published as 400 ft/min). The aircraft flew at high angles of attack, appearing "on the ragged edge of a stall" but remaining stall- and spin-proof, mushing downward controllably. Funding constraints limited further testing. ==Design features==