Wake Measurements behind an Oscillating Airfoil in Dynamic Stall Conditions

<table class="table-group" width="800px"><tr class="fig-image" id="a"><td><img alt="265429.fig.009a" src="https://static.hindawi.com/articles/isrn/volume-2013/265429/figures/265429.fig.009a.jpg"/></td></tr><tr class="fig-caption"><td align="center"><table><tr><td><b>(a) </b>Light dynamic stall</td></tr></table></td></tr><tr class="fig-image" id="b"><td><img alt="265429.fig.009b" src="https://static.hindawi.com/articles/isrn/volume-2013/265429/figures/265429.fig.009b.jpg"/></td></tr><tr class="fig-caption"><td align="center"><table><tr><td><b>(b) </b>Deep dynamic stall</td></tr></table></td></tr></table>

<table>Pressure differences measured upstream and downstream the airfoil; pressure taps located, respectively, 3 chords upstream the airfoil leading edge and 2 chords downstream the airfoil trailing edge.</table>

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Figure 9

Figure 9: Wake Measurements behind an Oscillating Airfoil in Dynamic Stall Conditions 