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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 C) and C(1) at locations X) & YD over the airfoil. cf 1003 0.9974 0.9893 0.9759 0.95733 0.93377 0.00157 0.00223 0.00419 0.00739 0.01172 0.01705 0.02323 0.03006 0.00432 0.0126 0.0165 0.0211 0.0313 0.0279 0.1911 0.2321 0.83591 0.79536 0.75154 0.7049 0.65595 0.03738 0.04498 0.05267 0.261 0.06025 0.067530.3452 0.5043 -0.5467 0.7654 0.9391 0.9453 1.0876 -0.4233 0.07431 0.0804 0.08562 0.08978 0.09272 0.55331 0.44811 0.39597 0.24722 0.20261 0.16142 0.12411 0.09112 0.06282 0.03952 0.02145 0.00878 0.00161 0.09366 0.0914 0.08736 0.08163 0.07438 0.0658 0.05615 0.04566 0.0346 0.02319 0.01161 1.3233 1.4203 1.7688 1.8716 2.0511 2.2698 2.3861 2.6653 -0.544 0.3443 MacBook Pro 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 C) and C(1) at locations X) & YD over the airfoil. cf 1003 0.9974 0.9893 0.9759 0.95733 0.93377 0.00157 0.00223 0.00419 0.00739 0.01172 0.01705 0.02323 0.03006 0.00432 0.0126 0.0165 0.0211 0.0313 0.0279 0.1911 0.2321 0.83591 0.79536 0.75154 0.7049 0.65595 0.03738 0.04498 0.05267 0.261 0.06025 0.067530.3452 0.5043 -0.5467 0.7654 0.9391 0.9453 1.0876 -0.4233 0.07431 0.0804 0.08562 0.08978 0.09272 0.55331 0.44811 0.39597 0.24722 0.20261 0.16142 0.12411 0.09112 0.06282 0.03952 0.02145 0.00878 0.00161 0.09366 0.0914 0.08736 0.08163 0.07438 0.0658 0.05615 0.04566 0.0346 0.02319 0.01161 1.3233 1.4203 1.7688 1.8716 2.0511 2.2698 2.3861 2.6653 -0.544 0.3443 MacBook Pro