Xenon 2
Role	Autogyro Type of aircraft
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

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

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)

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)