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Wind tunnel measurements of the pressure and skin friction around a NACA 2415 airfoil at 8 degrees angle of attack resulted in the following
data of pressure and skin friction coefficients Cp(I) and Cf(1) at locations X(I)/C & Y(1)/C over the airfoil. Point index(i) X(i/c YO/c Cp(i) Cr(i)
x 10-3 1 * * 0 0 2 0.95 -0.0013 0.2731 3 0.8 0.0037 ).2595 6 0.75 0.0062 ).2762 0.65 0.0087 0.3002 0.575 0.0105 0.3287 ).525 0.0... 

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