Three-dimensional (3-D) transition mechanism in a swept cylinder boundary-layer is studied experimentally in detail using an effective smoke visualization and a hot wire technique. Critical Reynolds number, which indicates the onset of the crossflow instability found to be smaller than the previous value, and the traveling disturbance which appears in the final stage of the transition is found to be the inflexional instability (secondary instability) being induced by the crossflow instability (primary instability). Guidelines for future Laminar Flow Control wing study on an Airbus wing are provided.
|Journal||Reports of the Laboratory for Air-Flow Measurements, the Institute of High Speed Mechanics, Tohoku University|
|Publication status||Published - 1988|
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