Consider the naca 0012 airfoil, the shape of which is shown at the top of fig. P41. The pressure coefficient distribution over the surface of the airfoil at zero angle of attack is shown at the bottom of fig. P41. These are low-speed values measured in a wind tunnel at re=3.65 x 10 6 . From this information, estimate the critical mach number of the naca 0012 airfoil at zero angle of attack.
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