Summary
Stability experiments are conducted in the ASU Unsteady Wind Tunnel on a 45° swept airfoil. The surface of the is polished to 0.25 μm rms. Under these conditions, natural stationary crossflow vortices are not measurable. This state is used to measure roughness-induced stationary crossflow. Spanwise arrays of 70–150 μm roughness elements are introduced near the attachment line. Detailed hot-wire measurements are taken to document the growth of these vortices. The data clearly show that linear stability theory does not accurately predict the growth rates of stationary crossflow waves under these conditions.
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Radeztsky, R.H., Reibert, M.S., Saric, W.S. (1995). Development of Stationary Crossflow Vortices on a Swept Wing. In: Kobayashi, R. (eds) Laminar-Turbulent Transition. IUTAM Symposia. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-79765-1_35
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DOI: https://doi.org/10.1007/978-3-642-79765-1_35
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