Airfoil: M6 (85%) Builder: L. Spychalla Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60600 Number of angles of attack: 49 alpha / Cl / Cm -6.57 -0.480 -0.0690 -5.24 -0.387 -0.0690 -4.20 -0.325 -0.0690 -3.13 -0.256 -0.0690 -2.12 -0.195 -0.0690 -1.07 -0.048 -0.0690 -0.05 0.007 -0.0690 1.00 0.196 -0.0690 1.89 0.319 -0.0690 2.94 0.432 -0.0690 4.01 0.517 -0.0690 5.11 0.602 -0.0690 6.06 0.673 -0.0690 7.17 0.761 -0.0690 8.05 0.825 -0.0690 9.16 0.871 -0.0690 10.14 0.909 -0.0690 11.22 0.956 -0.0690 12.07 0.985 -0.0690 13.16 0.983 -0.0690 14.18 0.924 -0.0690 15.17 0.841 -0.0690 16.00 0.841 -0.0690 17.07 0.839 -0.0690 18.14 0.835 -0.0690 16.53 0.839 -0.0690 15.69 0.865 -0.0690 14.65 0.842 -0.0690 13.68 0.993 -0.0690 12.64 1.013 -0.0690 11.56 0.993 -0.0690 10.67 0.952 -0.0690 9.68 0.901 -0.0690 8.62 0.862 -0.0690 7.50 0.789 -0.0690 6.62 0.718 -0.0690 5.49 0.629 -0.0690 4.40 0.544 -0.0690 3.56 0.471 -0.0690 2.48 0.377 -0.0690 1.41 0.238 -0.0690 0.28 0.048 -0.0690 -0.55 -0.050 -0.0690 -1.69 -0.124 -0.0690 -2.70 -0.241 -0.0690 -3.74 -0.299 -0.0690 -4.81 -0.369 -0.0690 -5.74 -0.430 -0.0690 -6.68 -0.489 -0.0690 Tabulated from data in file CL00665.DAT & reduced using program Q02.00L Average Reynolds #: 100700 Number of angles of attack: 49 alpha / Cl / Cm -6.62 -0.511 -0.0690 -5.31 -0.411 -0.0690 -4.16 -0.340 -0.0690 -3.28 -0.291 -0.0690 -2.14 -0.206 -0.0690 -1.21 -0.046 -0.0690 0.04 0.181 -0.0690 0.99 0.297 -0.0690 1.95 0.383 -0.0690 2.95 0.457 -0.0690 3.94 0.531 -0.0690 5.13 0.627 -0.0690 6.14 0.711 -0.0690 7.15 0.794 -0.0690 8.18 0.860 -0.0690 9.17 0.903 -0.0690 10.13 0.950 -0.0690 11.06 0.993 -0.0690 12.18 1.020 -0.0690 13.21 0.985 -0.0690 14.10 0.907 -0.0690 15.00 0.847 -0.0690 16.18 0.828 -0.0690 17.03 0.807 -0.0690 17.97 0.791 -0.0690 16.62 0.828 -0.0690 15.66 0.833 -0.0690 14.55 0.870 -0.0690 13.64 0.946 -0.0690 12.66 1.019 -0.0690 11.69 1.013 -0.0690 10.67 0.975 -0.0690 9.60 0.922 -0.0690 8.73 0.878 -0.0690 7.65 0.824 -0.0690 6.51 0.732 -0.0690 5.55 0.654 -0.0690 4.62 0.577 -0.0690 3.63 0.498 -0.0690 2.47 0.409 -0.0690 1.56 0.330 -0.0690 0.45 0.219 -0.0690 -0.53 0.064 -0.0690 -1.62 -0.152 -0.0690 -2.70 -0.262 -0.0690 -3.63 -0.301 -0.0690 -4.58 -0.359 -0.0690 -5.68 -0.434 -0.0690 -6.76 -0.518 -0.0690 Tabulated from data in file CL00714.DAT & reduced using program Q02.00L Average Reynolds #: 201300 Number of angles of attack: 49 alpha / Cl / Cm -6.70 -0.546 -0.0690 -4.97 -0.408 -0.0690 -4.24 -0.361 -0.0690 -3.02 -0.233 -0.0690 -1.80 -0.075 -0.0690 -0.99 -0.008 -0.0690 0.23 0.163 -0.0690 1.06 0.269 -0.0690 2.27 0.381 -0.0690 3.10 0.455 -0.0690 4.27 0.564 -0.0690 5.11 0.638 -0.0690 6.22 0.748 -0.0690 7.39 0.833 -0.0690 8.19 0.871 -0.0690 9.34 0.931 -0.0690 10.12 0.971 -0.0690 11.17 1.012 -0.0690 12.19 1.031 -0.0690 13.15 1.034 -0.0690 14.14 0.965 -0.0690 15.26 0.857 -0.0690 16.47 0.827 -0.0690 17.21 0.837 -0.0690 18.44 0.819 -0.0690 16.46 0.830 -0.0690 15.39 0.862 -0.0690 14.47 0.922 -0.0690 13.56 1.019 -0.0690 12.41 1.027 -0.0690 11.61 1.015 -0.0690 10.40 0.974 -0.0690 9.51 0.930 -0.0690 8.33 0.866 -0.0690 7.42 0.822 -0.0690 6.48 0.757 -0.0690 5.21 0.634 -0.0690 4.22 0.546 -0.0690 3.56 0.489 -0.0690 2.23 0.366 -0.0690 1.22 0.276 -0.0690 0.18 0.146 -0.0690 -0.86 -0.007 -0.0690 -1.89 -0.094 -0.0690 -2.90 -0.215 -0.0690 -3.80 -0.338 -0.0690 -4.79 -0.400 -0.0690 -5.74 -0.469 -0.0690 -6.67 -0.541 -0.0690 Tabulated from data in file CL00722.DAT & reduced using program Q02.00L Average Reynolds #: 302100 Number of angles of attack: 49 alpha / Cl / Cm -6.46 -0.541 -0.0690 -5.10 -0.437 -0.0690 -4.24 -0.372 -0.0690 -3.02 -0.213 -0.0690 -2.14 -0.113 -0.0690 -0.94 -0.020 -0.0690 0.03 0.078 -0.0690 0.88 0.229 -0.0690 1.86 0.344 -0.0690 3.00 0.456 -0.0690 4.11 0.560 -0.0690 4.91 0.633 -0.0690 6.05 0.731 -0.0690 7.05 0.802 -0.0690 8.01 0.851 -0.0690 9.03 0.912 -0.0690 10.18 0.975 -0.0690 11.10 1.012 -0.0690 12.24 1.037 -0.0690 13.48 1.057 -0.0690 14.22 1.012 -0.0690 15.60 0.889 -0.0690 16.50 0.835 -0.0690 17.33 0.812 -0.0690 18.25 0.826 -0.0690 16.19 0.838 -0.0690 15.17 0.914 -0.0690 14.29 0.974 -0.0690 13.53 1.039 -0.0690 12.50 1.047 -0.0690 11.45 1.013 -0.0690 10.31 0.972 -0.0690 9.52 0.931 -0.0690 8.31 0.858 -0.0690 7.44 0.812 -0.0690 6.05 0.721 -0.0690 5.56 0.682 -0.0690 4.10 0.549 -0.0690 3.12 0.458 -0.0690 2.12 0.362 -0.0690 1.23 0.261 -0.0690 0.19 0.107 -0.0690 -0.83 -0.021 -0.0690 -1.86 -0.092 -0.0690 -2.90 -0.201 -0.0690 -3.89 -0.332 -0.0690 -4.91 -0.426 -0.0690 -5.90 -0.496 -0.0690 -6.91 -0.570 -0.0690 Tabulated from data in file CL00724.DAT & reduced using program Q02.00L File m685.lft created on 09-12-1997 at 13:46:18 using program FORMAT