Single-seat single-engined parasol-winged aircraft with conventional three-axis control. Wing has unswept leading and trailing edges, and constant chord; V-tail. Pitch/yaw control by elevon; roll control by ailerons; wing profile Clark Y; double-surface. Undercarriage has three wheels in taildragger formation. Aluminium-tube/wood fuselage, partially enclosed. Engine mounted at wing height driving tractor propeller.
Began in 1974, it was not until July 1977 that the aircraft, a joint venture between Kazimierz Jarzab, S Kustron and S Wojton, made its first flight. It is a parasol-winged taildragger constructed largely from wood and aluminium alloy. The pilot sits under the wing, in an open cockpit but protected by a windscreen, and the two-blade pusher propeller is mounted at the trailing edge of the wing. A tubular empennage supports the V-tail, which has in addition two fins, shaped like an isosceles triangle with rounded corners.
Length overall 13.8 ft, 4.20 m.
Height overall 3.6ft, 1.10m.
Wing span 23.0ft, 7.0m.
Constant chord 2.8ft, 0.86m.
Sweepback 0 degs
Total wing area 65 sq.ft, 6.0 sq.m.
Wing aspect ratio 8.2/1.
Engine: MZ-250, 16 hp.
Power per unit area 0.25 hp/sq.ft, 2.7 hp/sq.m.
Fuel capacity 5.3 US gal, 4.4 Imp gal, 20.0 litre.
Empty weight 209 lb, 95kg.
Max take-off weight 419 lb, 190kg.
Payload 209 lb, 95 kg.
Max wing loading 6.45 lb/sq.ft, 31.7 kg/sq.m.
Max power loading 26.2 lb/hp, 11.9kg/hp.
Cruising speed 68mph, 110kph.
Max climb rate at sea level 400ft/min, 2.0mls.
Take-off distance 660ft, 200m.
Range at average cruising speed 622 mile, 1000km.