|The W.9 in April 1947|
|Manufacturer||Cierva Autogiro Company, Ltd.|
|Primary user||Air Ministry|
The Cierva W.9 was a British 1940s experimental helicopter with a three-blade tilting-hub controlled main rotor, and torque compensation achieved using a jet of air discharged from the rear port side of the fuselage.
In 1943 primary investor G & J Weir Ltd., revived the moribund Cierva Autogiro Company to develop an experimental helicopter to Air Ministry Specification E.16/43. The W.9 was to investigate James G. Weir's contention that a powered tilting hub controlled rotor with automatic collective pitch control, and torque reaction control using jet efflux, were both safer and more efficient than the Sikorsky R-4 helicopter fitted with manually controlled main rotor cyclic and collective pitch and the anti-torque tail rotor system. The W.9 was completed late in 1944 and assigned serial PX203. It was damaged during ground-running due to incorrect control phasing arising from a high order of pitch-flap coupling, and did not start test flying until 1945.
The most visible characteristic of the W.9 was torque compensation and directional control by using blown air rather than a tail propeller. A variable pitch fan cooled the engine; the heated air and engine exhaust passed through the long hollow tail boom and exhausted to port. Foot pedals controlled the fan pitch. Of more importance, however, was the hydraulically powered shaft-driven tilting rotor hub with rotational speed variation to give automatic collective pitch control. Development of the rotor system resulted in a tilting hub combined with cyclic pitch control of each blade to minimize control forces. Manual control of collective pitch was added to the automatic collective pitch change system to provide precise vertical control in hover and the ability to cushion a landing from an autorotative descent.
Data from Flight 
- Crew: 2
- Length: 37 ft (11 m)
- Height: 10 ft (3.0 m)
- Gross weight: 2,647 lb (1,201 kg)
- Powerplant: 1 × de Havilland Gipsy Queen 31 6-cyl. air-cooled in-line piston engine, 205 hp (153 kW)
- Main rotor diameter: 36 ft 0 in (10.97 m)
- Main rotor area: 1,017 sq ft (94.5 m2)
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The Illustrated Encyclopedia of Aircraft (Part Work 1982-1985). Orbis Publishing.