NACA0012 Airfoil in Re=1x10^6 Viscous Airflow with Incidence Varied From -20 to 20 Degrees

This shows a plot of the coefficient of pressure for the upper surface (yellow) and lower surface (blue) of a NACA0012 airfoil (upper plot) and a plot of the boundary layer seperation on the upper and lower surfaces (grey lines show the airfoil's geometry) (lower plot). As the video plays the incidence (angle of attack) is varied from -20 to 20 degrees. This was done using XFOIL, a airfoil analysis program developed by Mark Drela at MIT. (web.mit.edu ... airfoil aiflow xfoil naca0012 UCD ...

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