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Celier Kiss

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Kiss
Role Autogyro
National origin Poland
Manufacturer Celier Aviation
Designer Raphael Celier
Status In production

The Celier Kiss is a series of Polish autogyros that was designed by Frenchman Raphael Celier and produced by his company, Celier Aviation of Jaktorów-Kolonia, Poland. The aircraft is supplied as a kit for amateur construction or as a complete ready-to-fly-aircraft.[1]

Design and development

The tandem seat Kiss series was designed as a complement to the side-by-side configuration Celier Xenon 2 series of autogyros. The Kiss series all feature a single main rotor, tricycle landing gear, a low-set T-tail and a choice of engines, all mounted in pusher configuration.[1]

Variants

Kiss 582
A proposed single seat variant under development in 2011. It will be powered by the twin cylinder, liquid-cooled, two-stroke, dual-ignition 64 hp (48 kW) Rotax 582 engine. The cockpit will be either partially or, optionally, fully enclosed.[1]
Kiss 912
Base model, with two seats in tandem, powered by a four cylinder, air and liquid-cooled, four-stroke, dual-ignition 80 hp (60 kW) Rotax 912UL engine in pusher configuration. The cockpit has a semi-enclosed fairing with a windshield.[1]
Kiss 912S
Upgraded model, with two seats in tandem, powered by a four cylinder, air and liquid-cooled, four-stroke, dual-ignition 100 hp (75 kW) Rotax 912ULS engine in pusher configuration. The cockpit has a fully enclosed fairing.[1]
Kiss 914
Turbocharged model, with two seats in tandem, powered by a four cylinder, air and liquid-cooled, four-stroke, dual-ignition 115 hp (86 kW) Rotax 914 engine in pusher configuration. The cockpit has a fully enclosed fairing.[1]

Specifications (912)

Data from Bayerl[1]

General characteristics

  • Crew: one
  • Capacity: one passenger
  • Empty weight: 200 kg (441 lb)
  • Gross weight: 450 kg (992 lb)
  • Fuel capacity: 50 litres (11 imp gal; 13 US gal)
  • Powerplant: 1 × Rotax 912UL four cylinder, liquid and air-cooled, four stroke aircraft engine, 60 kW (80 hp)
  • Main rotor diameter: 8.4 m (27 ft 7 in)
  • Main rotor area: 55.4 m2 (596 sq ft)

Performance

  • Maximum speed: 140 km/h (87 mph, 76 kn)
  • Endurance: 3 hours
  • Rate of climb: 3 m/s (590 ft/min)
  • Disk loading: 8.1 kg/m2 (1.7 lb/sq ft)

References

  1. ^ a b c d e f g Bayerl, Robby; Martin Berkemeier; et al: World Directory of Leisure Aviation 2011-12, page 178. WDLA UK, Lancaster UK, 2011. ISSN 1368-485X
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