Experiments have been conducted to simulate the effects of the multiple orthogonal vortex interactions that may occur on the tail rotor of a helicopter. In these experiments, which represent an idealiaed form of the interaction problem, the surface oressure response durine the interaction
was measured on a symmetrical profile wine instrumented with a chordwise array of miniature pressure transducers. The wing was located one chord length downstream of another wing of identical profile. A vortex was generated upstream of these wings using a single‐bladed rotor rig, and
was then convected toward and subsequently “cut” by both wings. It was found that when the upstream wing was installed, the pressure response experienced by the instrumented wing was similar in form but reduced in magnitude by about half compared to the results obtained without
the npstream wing. This may indicate that the vortex has the ability to reconnect and re‐establish sipificant rotational and axial velocity components after an initial cut. The results also suggest that significant vibration and noise radiation from tail rotors may be produced from
multiple cuts of the same vortex.
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Document Type: Research Article
Department of Aerospace Engineering, The University of Glasgow, Glasgow G12 8QQ, UK
Publication date: 2001-07-01
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