Airfoil: M6 (65%) Builder: L. Spychalla Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60700 Number of angles of attack: 49 alpha / Cl / Cm -6.61 -0.507 -0.0270 -5.43 -0.426 -0.0270 -4.26 -0.344 -0.0270 -3.29 -0.270 -0.0270 -2.32 -0.193 -0.0270 -1.32 -0.045 -0.0270 -0.15 0.026 -0.0270 0.85 0.059 -0.0270 1.90 0.196 -0.0270 2.99 0.369 -0.0270 3.85 0.439 -0.0270 4.92 0.510 -0.0270 6.01 0.602 -0.0270 6.90 0.659 -0.0270 7.95 0.724 -0.0270 8.99 0.791 -0.0270 9.99 0.849 -0.0270 11.11 0.883 -0.0270 12.10 0.844 -0.0270 13.09 0.825 -0.0270 14.09 0.805 -0.0270 14.90 0.788 -0.0270 16.08 0.819 -0.0270 16.96 0.841 -0.0270 18.00 0.823 -0.0270 16.69 0.825 -0.0270 15.56 0.831 -0.0270 14.60 0.805 -0.0270 13.53 0.813 -0.0270 12.67 0.806 -0.0270 11.64 0.870 -0.0270 10.64 0.888 -0.0270 9.59 0.846 -0.0270 8.69 0.794 -0.0270 7.60 0.724 -0.0270 6.56 0.665 -0.0270 5.61 0.589 -0.0270 4.52 0.508 -0.0270 3.58 0.438 -0.0270 2.51 0.332 -0.0270 1.38 0.112 -0.0270 0.52 0.069 -0.0270 -0.66 0.027 -0.0270 -1.54 -0.094 -0.0270 -2.54 -0.182 -0.0270 -3.67 -0.274 -0.0270 -4.65 -0.349 -0.0270 -5.61 -0.418 -0.0270 -6.63 -0.494 -0.0270 Tabulated from data in file CF00757.DAT & reduced using program Q02.00L Average Reynolds #: 101000 Number of angles of attack: 49 alpha / Cl / Cm -6.70 -0.605 -0.0270 -5.28 -0.471 -0.0270 -4.35 -0.393 -0.0270 -3.29 -0.308 -0.0270 -2.23 -0.220 -0.0270 -1.18 -0.136 -0.0270 -0.10 0.021 -0.0270 0.76 0.075 -0.0270 1.85 0.264 -0.0270 2.95 0.370 -0.0270 4.04 0.455 -0.0270 5.01 0.533 -0.0270 6.11 0.619 -0.0270 6.97 0.679 -0.0270 8.05 0.756 -0.0270 9.11 0.827 -0.0270 10.14 0.883 -0.0270 11.13 0.888 -0.0270 11.93 0.896 -0.0270 13.11 0.876 -0.0270 14.03 0.834 -0.0270 14.95 0.826 -0.0270 16.00 0.830 -0.0270 17.08 0.815 -0.0270 17.99 0.852 -0.0270 16.58 0.825 -0.0270 15.62 0.822 -0.0270 14.69 0.862 -0.0270 13.56 0.840 -0.0270 12.65 0.836 -0.0270 11.67 0.900 -0.0270 10.59 0.889 -0.0270 9.54 0.842 -0.0270 8.68 0.788 -0.0270 7.55 0.709 -0.0270 6.64 0.646 -0.0270 5.50 0.559 -0.0270 4.58 0.486 -0.0270 3.46 0.398 -0.0270 2.53 0.322 -0.0270 1.44 0.185 -0.0270 0.50 0.023 -0.0270 -0.55 -0.010 -0.0270 -1.63 -0.175 -0.0270 -2.68 -0.261 -0.0270 -3.56 -0.333 -0.0270 -4.63 -0.417 -0.0270 -5.64 -0.506 -0.0270 -6.65 -0.594 -0.0270 Tabulated from data in file CF00759.DAT & reduced using program Q02.00L Average Reynolds #: 201700 Number of angles of attack: 49 alpha / Cl / Cm -6.50 -0.612 -0.0270 -5.40 -0.501 -0.0270 -4.38 -0.400 -0.0270 -3.19 -0.297 -0.0270 -2.15 -0.207 -0.0270 -1.26 -0.128 -0.0270 -0.29 -0.014 -0.0270 0.80 0.156 -0.0270 1.88 0.263 -0.0270 2.96 0.358 -0.0270 4.04 0.456 -0.0270 4.89 0.530 -0.0270 5.94 0.615 -0.0270 7.04 0.707 -0.0270 8.09 0.785 -0.0270 8.91 0.840 -0.0270 10.10 0.914 -0.0270 11.02 0.938 -0.0270 12.17 0.912 -0.0270 13.03 0.927 -0.0270 14.14 0.852 -0.0270 15.12 0.868 -0.0270 15.92 0.835 -0.0270 17.14 0.834 -0.0270 18.02 0.827 -0.0270 16.46 0.825 -0.0270 15.52 0.836 -0.0270 14.58 0.882 -0.0270 13.56 0.864 -0.0270 12.56 0.904 -0.0270 11.55 0.930 -0.0270 10.71 0.930 -0.0270 9.69 0.879 -0.0270 8.62 0.808 -0.0270 7.58 0.732 -0.0270 6.55 0.650 -0.0270 5.65 0.578 -0.0270 4.57 0.486 -0.0270 3.46 0.386 -0.0270 2.55 0.303 -0.0270 1.44 0.208 -0.0270 0.46 0.098 -0.0270 -0.67 -0.078 -0.0270 -1.68 -0.182 -0.0270 -2.59 -0.259 -0.0270 -3.74 -0.357 -0.0270 -4.64 -0.433 -0.0270 -5.66 -0.533 -0.0270 -6.59 -0.613 -0.0270 Tabulated from data in file CL00761.DAT & reduced using program Q02.00L Average Reynolds #: 302200 Number of angles of attack: 49 alpha / Cl / Cm -6.95 -0.654 -0.0270 -5.20 -0.491 -0.0270 -4.34 -0.408 -0.0270 -3.06 -0.295 -0.0270 -2.14 -0.213 -0.0270 -1.05 -0.090 -0.0270 -0.13 -0.002 -0.0270 0.82 0.129 -0.0270 1.95 0.260 -0.0270 2.95 0.371 -0.0270 3.86 0.455 -0.0270 4.90 0.547 -0.0270 6.05 0.636 -0.0270 6.88 0.704 -0.0270 7.89 0.784 -0.0270 9.00 0.864 -0.0270 9.98 0.927 -0.0270 10.95 0.966 -0.0270 12.02 0.961 -0.0270 12.94 0.956 -0.0270 14.01 0.904 -0.0270 14.97 0.845 -0.0270 16.05 0.862 -0.0270 17.01 0.865 -0.0270 18.04 0.860 -0.0270 16.42 0.858 -0.0270 15.59 0.839 -0.0270 14.46 0.869 -0.0270 13.66 0.910 -0.0270 12.40 0.957 -0.0270 11.58 0.964 -0.0270 10.79 0.960 -0.0270 9.64 0.905 -0.0270 8.73 0.841 -0.0270 7.63 0.760 -0.0270 6.61 0.678 -0.0270 5.53 0.592 -0.0270 4.58 0.514 -0.0270 3.49 0.417 -0.0270 2.41 0.313 -0.0270 1.39 0.201 -0.0270 0.36 0.056 -0.0270 -0.57 -0.041 -0.0270 -1.69 -0.172 -0.0270 -2.67 -0.265 -0.0270 -3.66 -0.351 -0.0270 -4.79 -0.451 -0.0270 -5.79 -0.547 -0.0270 -6.73 -0.632 -0.0270 Tabulated from data in file CL00763.DAT & reduced using program Q02.00L File m665.lft created on 09-12-1997 at 13:46:18 using program FORMAT