The effects of wake splitter plates on the flow past a circular cylinder in the range 10 4 < R <5×10 4

摘要: Experiments were carried out using models having L/D [les ] 2 and the resulting pressure distributions vortex shedding characteristics are presented. A simple visualization technique which provides explanations of some measured results is described. It concluded that splitter planes reduce drag markedly by stabilizing separation points produce a wake narrower than for plain cylinder, raise base as much 50% affect Strouhal number to lesser degree. Careful measurement techniques have enabled these effects be presented accurately.