TYPE: Side-by-side ultralight.

PROGRAMME: Designed by Kappa 77 company and Institute of Aerospace Engineering at Brno Technical University and developed over a 22-month period. Initially named Kappa Sova (Owl). First of two flying prototypes (OK-BUU 23) first flown 26 May 1996; first public demonstration the following month at Jihlava Aero '96. Czech certification 23 September 1997; German certification, and of kit by FAA, in June 1999, followed by Polish certification in April 2001, Portuguese in June 2002, Australian at end 2003, Spanish certification planned for 2006. Approved for use in Brazil, Canada, Ecuador, Finland, France, Italy, Netherlands, South Africa and Spain.
Following Kappa’s bankruptcy in 2004, production continued by Jihlavan Airplanes under new name of Rapid and with modifications including new shape of engine cowling; revised canopy locking and cockpit seating arrangements, and electrically operated Fowler flaps.

CURRENT VERSIONS: KP-2U Rapid 200: As described. Available as Master baseline version, or as Major, with additional avionics and features.
KP-5 ASA Rapid 500: See separate entry.

CUSTOMERS: Over 140 sold by end 2005; customers in Belgium, Brazil, Czech Republic, Ecuador, Finland, France, Germany (known as KPD-2U), Italy, Netherlands, Poland, Portugal, Spain, South Africa and USA.

COSTS: Master EUR59,800; Major EUR65,000; both excluding tax. flyaway (2006).

DESIGN FEATURES: Low-wing monoplane conforming to BFU 95 regulations. Tapered wing with swept tips; sweptback fin with low tailplane.
Wing sections NACA GA(W)-1 at root and GA(W)-2 at tip; dihedral 6°. Fin and tailplane sections NACA 0012.

FLYING CONTROLS: Conventional and manual. Aileron actuation by pushrods. Electrically operated trim tab in port elevator; manually or electrically operated Fowler flaps (deflection 10 and 35°).

STRUCTURE: All-metal, except for CFRP cockpit frame. Two-spar wings detachable for storage. Fuselage constructed from Dural L-shape stringers, riveted bulkheads and Dural skin.

LANDING GEAR: Electrically retractable tricycle type (all units rearward) with manual override; rubber shock-absorption; mainwheels semi-exposed when retracted. Steerable nosewheel; hydraulic brakes. Fixed gear optional.

POWER PLANT: One 59.6 kW (79.9 hp) Rotax 912 UL engine, with 4:1 reduction drive to a three-blade ground adjustable pitch propeller; can alternatively accommodate 73.5 kW (98.6 hp) Rotax 912 ULS or 84.5 kW (113.3 hp) Rotax 914 and be fitted with Kaspar or Wcomp Varia two-blade flight adjustable propellers; from 2006, 59.7 kW (80 hp) Jabiru 2200 added to options. Fuel capacity (two wing centre-section tanks) 64 litres (16.9 US gallons; 14.1 Imp gallons). Optional two additional tanks each 15 litres (4.0 US gallons; 3.3 Imp gallons). Max fuel capacity 94 litres (24.8 US gallons; 20.7 Imp gallons).

ACCOMMODATION: Forward-hinged canopy. Dual controls. Starboard seat staggered rearwards 20 cm (8 in). Space behind seats for 30 kg (66 lb) of baggage.

EQUIPMENT: Optional emergency system under consideration.


  • Wing span: 9,90 m (32 ft 5¾ in)
  • Length overall: 7,165 m (23 ft 6 in)
  • Height overall: 2,60 m (8 ft 6¼ in)
  • Propeller diameter: 1,73 m (5 ft 8 in)


  • Wings, gross: 11,85 m² (127.6 sq ft)


  • Weight empty: 282 kg (622 lb)
  • Max T-O weight: 472.5 kg (1,041 lb)

PERFORMANCE (Rotax 912 UL engine):

  • Max level speed: 129 kt (240 km/h; 149 mph)
  • Max cruising speed at 75% power: 108 kt (200 km/h; 124 mph)
  • Stalling Speed: flaps up: 39 kt (71 km/h; 45 mph)
    • flaps down: 26 kt (48 km/h; 30 mph)
  • Max rate of climb at S/L: 390 m (1,279 ft)/min
  • T-O run: 100 m (330 ft)
  • Landing run: 140 m (460 ft)
  • Range with max fuel: 518 n miles (960 km; 596 miles)
  • g limits: +4/-2