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Celier Xenon 2
Celier Xenon 2
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Celier Xenon 2

Xenon 2
Role Autogyro
National origin Poland
Manufacturer Celier Aviation
Designer Raphael Celier
Status Production completed
Number built 100 (2011)

The Celier Xenon 2 (also referred to by the manufacturer as the Xenon II) is a series of Polish autogyros that was designed by Frenchman Raphael Celier and produced by his company, Celier Aviation of Piotrków Trybunalski, Poland. The aircraft is supplied as a kit for amateur construction or as a complete ready-to-fly-aircraft.[1][2]

Production of the Xenon 2 has ended and only the Celier Xenon 4 model remained in production is 2017.

Design and development

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The side-by-side configuration Xenon 2 complements the tandem seat Celier Kiss series of autogyros. The Xenon 2 series all feature a single main rotor, tricycle landing gear, a low-set twin-boom T-tail, a fully enclosed two seat cockpit and a choice of engines, all mounted in pusher configuration.[1]

One hundred Xenon 2s had been completed by 2011. The design has been developed into the three seat Celier Xenon 3 and Xenon 4.[1]

Variants

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Xenon 2 RT
Turbocharged model, powered by a four cylinder, air and liquid-cooled, four-stroke, dual-ignition 115 hp (86 kW) Rotax 914 engine in pusher configuration.[1]
Xenon 2R Eco
Model powered by a four cylinder, air and liquid-cooled, four-stroke, dual-ignition 100 hp (75 kW) Rotax 912ULS engine in pusher configuration.[1]
Xenon 2 Executive
Upgraded turbocharged model, powered by a four cylinder, air and liquid-cooled, four-stroke, dual-ignition 135 hp (101 kW) Rotax 914 engine in pusher configuration. The aircraft has many upgrades and optional equipment as standard, including a Mitsubishi turbocharger that boosts the engine power output.[1]
Xenon 3
Development version
Xenon 4
Further refined three-seat version[3]

Specifications (Xenon 2 RT)

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Celier Xenon 2

Data from Bayerl[1]

General characteristics

  • Crew: one
  • Capacity: one passenger
  • Empty weight: 285 kg (628 lb)
  • Gross weight: 450 kg (992 lb)
  • Fuel capacity: 85 litres (19 imp gal; 22 US gal)
  • Powerplant: 1 × Rotax 914 four cylinder, liquid and air-cooled, four stroke turbocharged aircraft engine, 86 kW (115 hp)
  • Main rotor diameter: 8.4 m (27 ft 7 in)
  • Main rotor area: 55.4 m2 (596 sq ft)

Performance

  • Maximum speed: 195 km/h (121 mph, 105 kn)
  • Cruise speed: 160 km/h (99 mph, 86 kn)
  • Rate of climb: 8 m/s (1,600 ft/min)

References

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