Celier Kiss
| Kiss | |
|---|---|
| Role | Autogyro |
| National origin | Poland |
| Manufacturer | Celier Aviation |
| Designer | Raphael Celier |
| Status | In production |
| Unit cost |
€29,900 (Kiss 912, assembled, 2011) |
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
External links
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