Airfoil: NACA 2415 Builder: D. Imes Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60700 Number of angles of attack: 49 alpha / Cl / Cm -6.05 -0.494 -0.0530 -4.64 -0.398 -0.0530 -3.46 -0.285 -0.0530 -2.56 -0.171 -0.0530 -1.63 -0.038 -0.0530 -0.42 0.073 -0.0530 0.64 0.141 -0.0530 1.45 0.221 -0.0530 2.65 0.337 -0.0530 3.48 0.418 -0.0530 4.74 0.547 -0.0530 5.58 0.642 -0.0530 6.71 0.789 -0.0530 7.73 0.880 -0.0530 8.71 0.953 -0.0530 9.77 1.006 -0.0530 10.72 1.043 -0.0530 11.87 1.099 -0.0530 12.80 1.129 -0.0530 13.70 1.149 -0.0530 14.69 0.702 -0.0530 15.57 0.712 -0.0530 16.60 0.724 -0.0530 17.77 0.745 -0.0530 18.70 0.842 -0.0530 17.07 0.726 -0.0530 16.11 0.721 -0.0530 15.15 0.726 -0.0530 14.18 0.696 -0.0530 13.24 0.733 -0.0530 12.24 0.735 -0.0530 11.25 1.073 -0.0530 10.19 1.029 -0.0530 9.17 0.984 -0.0530 8.27 0.936 -0.0530 7.14 0.845 -0.0530 6.27 0.766 -0.0530 5.22 0.638 -0.0530 4.20 0.503 -0.0530 2.99 0.334 -0.0530 2.16 0.276 -0.0530 0.93 0.181 -0.0530 0.01 0.135 -0.0530 -1.02 0.036 -0.0530 -1.99 -0.068 -0.0530 -3.15 -0.241 -0.0530 -4.04 -0.339 -0.0530 -5.21 -0.437 -0.0530 -6.05 -0.484 -0.0530 Tabulated from data in file CL00781.DAT & reduced using program Q02.00L Average Reynolds #: 101100 Number of angles of attack: 49 alpha / Cl / Cm -6.09 -0.518 -0.0530 -4.56 -0.298 -0.0530 -3.58 -0.162 -0.0530 -2.61 -0.051 -0.0530 -1.39 0.063 -0.0530 -0.45 0.141 -0.0530 0.49 0.274 -0.0530 1.75 0.468 -0.0530 2.58 0.520 -0.0530 3.70 0.613 -0.0530 4.66 0.698 -0.0530 5.65 0.784 -0.0530 6.68 0.867 -0.0530 7.85 0.957 -0.0530 8.89 1.025 -0.0530 9.72 1.063 -0.0530 10.71 1.103 -0.0530 11.79 1.148 -0.0530 12.78 1.176 -0.0530 13.65 1.188 -0.0530 14.49 0.767 -0.0530 15.65 0.730 -0.0530 16.60 0.711 -0.0530 17.57 0.784 -0.0530 18.70 0.823 -0.0530 17.15 0.740 -0.0530 16.13 0.747 -0.0530 15.08 0.737 -0.0530 14.08 0.769 -0.0530 13.12 0.821 -0.0530 12.38 1.173 -0.0530 11.28 1.125 -0.0530 10.31 1.081 -0.0530 9.33 1.034 -0.0530 8.32 0.985 -0.0530 7.26 0.904 -0.0530 6.14 0.812 -0.0530 5.12 0.724 -0.0530 4.02 0.627 -0.0530 3.17 0.555 -0.0530 2.13 0.479 -0.0530 1.07 0.378 -0.0530 -0.01 0.178 -0.0530 -1.06 0.087 -0.0530 -2.14 -0.012 -0.0530 -3.01 -0.099 -0.0530 -4.11 -0.239 -0.0530 -5.20 -0.394 -0.0530 -6.06 -0.494 -0.0530 Tabulated from data in file CL00783.DAT & reduced using program Q02.00L Average Reynolds #: 201700 Number of angles of attack: 49 alpha / Cl / Cm -6.04 -0.376 -0.0530 -4.31 -0.190 -0.0530 -3.58 -0.129 -0.0530 -2.52 -0.042 -0.0530 -1.46 0.053 -0.0530 -0.44 0.153 -0.0530 0.55 0.243 -0.0530 1.52 0.345 -0.0530 2.70 0.507 -0.0530 3.64 0.625 -0.0530 4.60 0.715 -0.0530 5.64 0.811 -0.0530 6.66 0.897 -0.0530 7.69 0.968 -0.0530 8.67 1.027 -0.0530 9.66 1.079 -0.0530 10.84 1.135 -0.0530 11.77 1.172 -0.0530 12.91 1.200 -0.0530 13.78 1.214 -0.0530 14.79 1.226 -0.0530 15.82 1.222 -0.0530 16.59 0.749 -0.0530 17.59 0.735 -0.0530 18.53 0.773 -0.0530 16.97 0.756 -0.0530 16.05 0.744 -0.0530 15.23 0.754 -0.0530 14.12 0.755 -0.0530 13.25 1.205 -0.0530 12.25 1.181 -0.0530 11.27 1.148 -0.0530 10.32 1.108 -0.0530 9.12 1.042 -0.0530 8.33 0.997 -0.0530 7.25 0.930 -0.0530 6.13 0.845 -0.0530 5.23 0.763 -0.0530 4.10 0.655 -0.0530 3.09 0.557 -0.0530 1.94 0.387 -0.0530 0.88 0.260 -0.0530 0.03 0.184 -0.0530 -1.14 0.076 -0.0530 -2.04 -0.007 -0.0530 -3.04 -0.091 -0.0530 -4.29 -0.194 -0.0530 -5.06 -0.260 -0.0530 -6.25 -0.401 -0.0530 Tabulated from data in file CL00785.DAT & reduced using program Q02.00L Average Reynolds #: 302500 Number of angles of attack: 49 alpha / Cl / Cm -6.11 -0.351 -0.0530 -4.52 -0.218 -0.0530 -3.57 -0.137 -0.0530 -2.66 -0.057 -0.0530 -1.47 0.057 -0.0530 -0.42 0.153 -0.0530 0.61 0.263 -0.0530 1.53 0.370 -0.0530 2.49 0.487 -0.0530 3.45 0.627 -0.0530 4.54 0.730 -0.0530 5.57 0.820 -0.0530 6.60 0.904 -0.0530 7.49 0.965 -0.0530 8.60 1.038 -0.0530 9.70 1.102 -0.0530 10.60 1.147 -0.0530 11.71 1.190 -0.0530 12.69 1.221 -0.0530 13.62 1.247 -0.0530 14.60 1.271 -0.0530 15.73 1.292 -0.0530 16.68 1.303 -0.0530 17.63 1.299 -0.0530 18.04 0.788 -0.0530 17.12 0.772 -0.0530 16.21 0.796 -0.0530 15.25 0.805 -0.0530 14.69 1.273 -0.0530 13.39 1.240 -0.0530 12.34 1.210 -0.0530 11.35 1.177 -0.0530 10.31 1.132 -0.0530 9.29 1.077 -0.0530 8.28 1.016 -0.0530 7.24 0.947 -0.0530 6.29 0.882 -0.0530 5.15 0.790 -0.0530 4.17 0.701 -0.0530 3.05 0.580 -0.0530 2.07 0.431 -0.0530 0.98 0.313 -0.0530 0.05 0.206 -0.0530 -1.01 0.097 -0.0530 -2.13 -0.011 -0.0530 -3.22 -0.113 -0.0530 -4.17 -0.197 -0.0530 -5.11 -0.276 -0.0530 -6.25 -0.375 -0.0530 Tabulated from data in file CL00787.DAT & reduced using program Q02.00L File naca2415.lft created on 09-12-1997 at 13:46:18 using program FORMAT