The aircraft was designed to provide viable heavy load lifting capability for commercial operations. It employed 3 main rotors all rotating in the same direction. Torque offset was provided by thrust components from the 3 rotors through built-in shaft tilt. The aircraft had a semi-monoquoque structure, a single engine, and a long-stroke undercarriage (5ft) to cope with high rates of descent. A description of the aircraft and its characteristics can be found in the following references,
Source: "The Cierva W-11 Air Horse", J. Gordon Leishman, VERTIFLITE Spring 2003, Page 52
Source: "Discussing the Helicopter", FLIGHT Staff, FLIGHT, December 2nd 1948, Pages 665-668
Design authority: Cierva Autogiro Company Ltd.
Primary manufacturer: Cierva Autogiro Company Ltd.
Parent type: Cierva Air Horse
Aircraft status: No longer flying
VTOL type: Helicopter
Lift devices: 3 in Multi-rotor configuration
Crew required: 2 in Side-by-side arrangement
Landing gear: Wheels (non-retractable)