Flow Observations and Analysis of NACA 0012 Aerofoil----no Leading Edge Vortex.
The flow fields for the NACA 0012 aerofoil at different angles of attack are shown in the velocity scenes above(Figure 1). The flow is generally attached along the aerofoil surface. The velocity decreases as the flow goes downstream along the aerofoil surface.
The mean wall shear stress coefficient for angle of attack 2 degrees (see Figure 3) shows that the flow separates from the surface at 76% of the chord length . This separation point moves upstream as the angle of attack increases (see Figure 1). The flow is in a steady state which can be seen in Figure 2 as the variations through time are inconspicuous. However, most importantly, the leading edge vortex does not exist over the NACA 0012 aerofoil. |
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