A helicopter tail rotor is required to provide yaw control and essentially that alone. However, it is expected to achieve that role when placed in an aerodynamically difficult location on the aircraft and to operate in a severe aerodynamic environment. This paper describes the pedal travel behaviour caused by aerodynamic interaction between the main rotor wake, the sideways velocity and subsequent forces generated by the tail boom noticed in Sea King helicopters, operating in extreme conditions during the Falklands war. Using earlier research which showed the effectiveness of a modification – a strake – to interrupt the air flow over the tail boom, conducts tests to examine the flow, the effects of the modification, and the side suction force. It also finds that the strake provides a simple and cost‐effective solution to the problem.
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