Airfoil: AG455ct-02r fp24.6 Builder: M. Drela, et al. Comment: Clean, Flap = 24.6° Number of Reynolds #'s: 4 Average Reynolds #: 100445.3 Number of angles of attack: 45 alpha / Cl / Cm -10.22 -0.14 -0.0852 -9.15 0.34 -0.2146 -7.95 0.44 -0.2174 -7.21 0.51 -0.2223 -6.13 0.59 -0.2203 -5.06 0.68 -0.2129 -4.07 0.75 -0.2089 -3.04 0.85 -0.2089 -2.07 0.94 -0.2087 -1.05 1.01 -0.2005 -0.10 1.06 -0.1956 1.01 1.34 -0.2148 1.96 1.32 -0.1969 3.11 1.33 -0.1808 4.06 1.37 -0.1736 5.06 1.41 -0.1639 6.13 1.44 -0.1533 7.02 1.50 -0.1932 8.01 1.48 -0.2456 8.90 1.39 -0.2656 9.95 1.32 -0.2757 10.91 1.33 -0.2879 11.96 1.32 -0.2884 11.71 1.32 -0.2772 10.68 1.31 -0.2702 9.67 1.35 -0.2669 8.70 1.40 -0.2479 7.83 1.46 -0.2283 6.80 1.51 -0.1560 5.92 1.46 -0.1499 4.79 1.41 -0.1578 3.75 1.36 -0.1672 2.73 1.33 -0.1761 1.74 1.33 -0.1874 0.73 1.33 -0.2028 -0.25 1.07 -0.1836 -1.29 1.01 -0.1920 -2.38 0.91 -0.1950 -3.40 0.83 -0.1992 -4.30 0.74 -0.1969 -5.33 0.66 -0.2065 -6.65 0.59 -0.2165 -7.55 0.53 -0.2150 -8.78 0.40 -0.2107 -9.53 0.31 -0.1980 Tabulated from data in file 06801gw.dat & reduced using program C10.20 Average Reynolds #: 201194.9 Number of angles of attack: 41 alpha / Cl / Cm -10.04 0.48 -0.2501 -9.20 0.57 -0.2535 -8.12 0.65 -0.2505 -7.21 0.71 -0.2473 -6.17 0.74 -0.2375 -5.11 0.72 -0.2204 -4.13 0.80 -0.2171 -3.11 0.89 -0.2132 -2.08 0.96 -0.2060 -1.08 1.06 -0.2056 0.02 1.32 -0.2165 0.95 1.32 -0.2048 1.96 1.33 -0.1924 3.08 1.37 -0.1814 4.13 1.42 -0.1743 5.15 1.48 -0.1675 6.13 1.51 -0.1584 7.06 1.59 -0.2000 7.97 1.58 -0.2376 9.02 1.50 -0.2715 10.02 1.36 -0.2817 9.63 1.42 -0.2761 8.75 1.49 -0.2639 7.79 1.57 -0.2318 6.82 1.57 -0.1833 5.76 1.50 -0.1582 4.84 1.47 -0.1662 3.72 1.41 -0.1725 2.81 1.36 -0.1790 1.75 1.32 -0.1894 0.78 1.32 -0.2017 -0.32 1.33 -0.2192 -1.31 1.02 -0.1974 -2.29 0.95 -0.2042 -3.39 0.89 -0.2134 -4.40 0.79 -0.2158 -5.46 0.71 -0.2197 -6.47 0.75 -0.2370 -7.42 0.71 -0.2466 -8.46 0.64 -0.2500 -9.50 0.56 -0.2532 Tabulated from data in file 06802gw.dat & reduced using program C10.20 Average Reynolds #: 301335.0 Number of angles of attack: 33 alpha / Cl / Cm -10.25 0.74 -0.2808 -9.18 0.85 -0.2840 -8.10 0.95 -0.2827 -7.20 0.86 -0.2679 -6.21 0.91 -0.2618 -5.07 0.95 -0.2507 -4.07 0.95 -0.2350 -2.98 0.99 -0.2232 -1.98 1.04 -0.2141 -0.96 1.30 -0.2274 0.02 1.30 -0.2112 1.09 1.32 -0.1999 2.02 1.35 -0.1911 3.13 1.42 -0.1844 4.12 1.46 -0.1767 5.19 1.53 -0.1711 6.24 1.55 -0.1603 5.73 1.54 -0.1642 4.79 1.50 -0.1718 3.78 1.45 -0.1772 2.77 1.39 -0.1852 1.73 1.34 -0.1910 0.76 1.31 -0.2010 -0.36 1.29 -0.2125 -1.31 1.32 -0.2392 -2.42 0.99 -0.2122 -3.49 0.99 -0.2289 -4.49 0.96 -0.2408 -5.43 0.96 -0.2557 -6.49 0.90 -0.2633 -7.53 1.00 -0.2800 -8.59 0.91 -0.2825 -9.54 0.82 -0.2835 Tabulated from data in file 06803gw.dat & reduced using program C10.20 Average Reynolds #: 402141.2 Number of angles of attack: 33 alpha / Cl / Cm -10.11 0.78 -0.2833 -9.11 0.87 -0.2829 -8.07 0.97 -0.2814 -7.16 1.04 -0.2795 -6.04 1.13 -0.2748 -5.12 1.20 -0.2715 -4.05 1.10 -0.2543 -3.10 1.13 -0.2450 -1.91 1.26 -0.2408 -0.99 1.25 -0.2176 -0.09 1.28 -0.2085 1.10 1.33 -0.2006 2.13 1.38 -0.1925 3.04 1.42 -0.1849 4.13 1.49 -0.1779 5.20 1.54 -0.1696 6.05 1.58 -0.1640 5.81 1.57 -0.1657 4.70 1.52 -0.1739 3.65 1.46 -0.1791 2.62 1.40 -0.1865 1.72 1.35 -0.1923 0.71 1.31 -0.2012 -0.35 1.27 -0.2102 -1.49 1.26 -0.2285 -2.47 1.31 -0.2597 -3.36 1.12 -0.2461 -4.36 1.25 -0.2666 -5.49 1.18 -0.2731 -6.47 1.10 -0.2774 -7.50 1.02 -0.2814 -8.56 0.92 -0.2824 -9.70 0.82 -0.2831 Tabulated from data in file 06804gw.dat & reduced using program C10.20 File ag455ct_fp25_lift.dat created using program clcm dist V1.1 on 30-Mar-2012 09:46:57