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Experimental investigation of the vorticity amplification on a swept wing with a blunt leading edge

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Figure

Figure 1: Coherent structures at the stagnation point of aHiemenz flow [6].
Figure 3: Blunt leading-edge wing mounted in the windtunnel
Figure 6: Natural case- a)Velocity along the attachmentline. b)Root Mean Square (RMS) of the velocity alongthe attachment line.
Figure 8: Normalised PSD inside the boundary layer atFigure 7position of coordinates (0.38,8,0).4.3
+2

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