Sud-Ouest_Ariel Knowpia

Ariel
Role	Experimental light helicopter
National origin	France
Manufacturer	Sud-Ouest
First flight	1947

The Sud-Ouest Ariel is a French two-seat light helicopter designed and built by Sud-Ouest. The helicopter rotors were driven by compressed-air jets at the end of each blade.^[1]

Design and development edit

The S.O.1100 Ariel I was first flown in 1947, it was a light all-metal helicopter with an enclosed two-seat cabin. Power was provided by a Mathis G8 engine which drove a Turbomeca compressor. The low-pressure air output from the compressor was ducted to each of the three rotor blades to the ends of each blade. At the tip of each blade was a combustion chamber where the air was mixed with fuel and ignited. The Ariel had a short tail boom with twin vertical tail surfaces.^[1] On 23 March 1949. an improved S.O.1110 Ariel II was flown, it was a similar configuration to the Ariel I was had revised tail surfaces.^[2]

The final variant was the S.O.1120 Ariel III which had a combined Turbomeca Arrius turbine-compressor rather than the two units of the earlier aircraft. With the space made from the power changes an extra seat was fitted. Another difference was the tail unit, the Ariel II had a single fin and rudder and used jet efflux from the turbine to provide directional control, a directional vane linked to the rudder directed the efflux.^[1]

Operational history edit

The Ariel was not put into production but the knowledge gained was used in the development of the Sud-Ouest Djinn.^[1]

Variants edit

S.O.1100 Ariel I: Two-seat experimental tip-jet helicopter with a piston engine-powered compressor.^[3]
S.O.1110 Ariel II: Improved variant with revised tail surfaces.
S.O.1120 Ariel III: Improved three-seat variant with a combined turbine-compressor.

Specifications (Ariel II) edit

Data from The Illustrated Encyclopedia of Aircraft^[1]

General characteristics

Crew: Two
Length: 7.15 m (23 ft 5 in)
Empty weight: 725 kg (1,598 lb)
Gross weight: 1,080 kg (2,380 lb)
Powerplant: 1 × Mathis G8 piston engine driving a compressor , 220 kW (164 hp)
Main rotor diameter: 10.80 m (35 ft 5.25 in)

Performance

Maximum speed: 170 km/h (105 mph, 91 kn)
Range: 300 km (186 mi, 162 nmi)

References edit

Notes edit

^ ^a ^b ^c ^d ^e Orbis 1985, p. 2975.
^ Apostolo 1984, p. 94.
^ Bridgman, Leonard, ed. (1947). Jane's all the World's Aircraft 1947. London: Sampson Low, Marston & Co. p. 143c.

Bibliography edit

Apostolo, Giorgio. The Illustrated Encyclopedia of Helicopters. New York: Bonanza Books, 1984. ISBN 0-517-439352.
Taylor, John W. R. and Jean Alexander. Combat Aircraft of the World. New York: G.P. Putnam's Sons, 1969. ISBN 0-71810-564-8.