The prototype Orlik was flown for the first time on 22 February 1987. Plans are available to amateur builders. Some glassfibre wing and fuselage components became available in 1989.

TYPE: Single-seat homebuilt.

AIRFRAME: Wing section NACA 23012. Wings of mostly wood construction, with plywood D-section leading-edge and fabric covering aft of spar. Welded steel tube forward fuselage; wooden semi-monocoque rear fuselage. Non-retractable tailwheel landing gear.

POWER PLANT: One 48.5 kW (65 hp) Walter Mikron III. Fuel capacity 30 litres (7.9 US gallons; 6.6 Imp gallons).

DIMENSIONS, EXTERNAL:

• Wing span: 7.60 m (24 ft 11¼ in)
• Length overall: 5.50 m (18 ft 0½ in)
• Height overall: 1.95 m (6 ft 4¾ in)
• Propeller diameter: 1.45 m (4 ft 9 in)

AREA:

• Wings, gross: 8.75 m² (94.18 sq ft)

WEIGHTS:

• Weight empty: 220 kg (485 lb)
• Max T-O weight: 320 kg (705 lb)

PERFORMANCE:

• Max level speed at S/L: 81 knots (150 km/h; 93 mph)
• Econ cruising speed at S/L: 49 knots (90 km/h; 56 mph)
• Stalling speed: 39 knots (7l km/h; 45 mph)
• Max rate of climb at S/L: 300 m (985 ft)/min
• T-O run: 100 m (328 ft)
• Landing run: 200 m (656 ft)
• Range, 20 min reserves: 215 nm (400 km; 248 miles)
• Endurance, 20 min reserves: 4 h 40 min