Airfoil: W1015-20 fp55 Builder: S. Cassidy Comment: Clean, Cf/C = 20%, Flap = 55° Number of Reynolds #'s: 3 Average Reynolds #: 99904.7 Number of angles of attack: 49 alpha / Cl / Cm -10.12 -0.08 -0.1118 -9.15 0.04 -0.1253 -8.29 0.14 -0.1375 -7.12 0.25 -0.1326 -6.12 0.35 -0.1383 -5.07 0.46 -0.1440 -4.16 0.58 -0.1520 -3.01 0.73 -0.1682 -2.12 0.83 -0.1739 -1.09 0.96 -0.1870 0.00 1.09 -0.1930 1.06 1.17 -0.1874 2.12 1.26 -0.1882 2.95 1.31 -0.1845 4.05 1.41 -0.1809 5.13 1.47 -0.1763 6.17 1.55 -0.1744 7.14 1.62 -0.1712 8.21 1.69 -0.1677 9.29 1.73 -0.1611 10.21 1.75 -0.1571 11.00 1.24 -0.2766 11.97 1.29 -0.2865 12.94 1.31 -0.2942 13.85 1.33 -0.3004 13.66 1.34 -0.2840 12.77 1.36 -0.2801 11.60 1.27 -0.2646 10.79 1.27 -0.2573 9.62 1.29 -0.2546 8.76 1.28 -0.2489 7.77 1.28 -0.2326 6.85 1.62 -0.1609 5.81 1.55 -0.1593 4.91 1.49 -0.1628 3.71 1.41 -0.1642 2.87 1.34 -0.1628 1.67 1.23 -0.1639 0.83 1.17 -0.1636 -0.31 1.07 -0.1670 -1.35 0.94 -0.1567 -2.38 0.82 -0.1511 -3.44 0.69 -0.1429 -4.30 0.58 -0.1338 -5.46 0.45 -0.1252 -6.32 0.35 -0.1177 -7.52 0.24 -0.1114 -8.47 0.15 -0.1129 -9.54 -0.01 -0.0864 Tabulated from data in file 07053gw.dat & reduced using program C10.20 Average Reynolds #: 200036.3 Number of angles of attack: 51 alpha / Cl / Cm -10.20 0.27 -0.2278 -9.16 0.37 -0.2309 -8.23 0.48 -0.2351 -7.13 0.59 -0.2354 -6.16 0.67 -0.2320 -5.23 0.74 -0.2292 -4.06 0.83 -0.2229 -3.06 0.91 -0.2168 -2.13 0.99 -0.2144 -1.10 1.06 -0.2047 -0.01 1.13 -0.1966 0.94 1.22 -0.1970 1.93 1.28 -0.1903 3.04 1.38 -0.1904 4.04 1.45 -0.1858 5.08 1.53 -0.1850 6.17 1.62 -0.1822 7.21 1.69 -0.1782 8.27 1.77 -0.1770 9.14 1.81 -0.1720 10.24 1.88 -0.1704 11.21 1.82 -0.1590 12.07 1.66 -0.1692 12.81 1.33 -0.2921 13.88 1.35 -0.3027 14.88 1.39 -0.3109 14.73 1.36 -0.3029 13.78 1.34 -0.2945 12.70 1.32 -0.2854 11.70 1.30 -0.2769 10.73 1.30 -0.2688 9.64 1.37 -0.2661 9.12 1.83 -0.1688 7.85 1.75 -0.1705 6.85 1.68 -0.1739 5.84 1.59 -0.1748 4.81 1.53 -0.1791 3.89 1.45 -0.1801 2.74 1.36 -0.1842 1.81 1.29 -0.1880 0.82 1.21 -0.1889 -0.35 1.11 -0.1925 -1.34 1.05 -0.2010 -2.40 0.96 -0.2052 -3.43 0.89 -0.2127 -4.42 0.80 -0.2172 -5.46 0.73 -0.2234 -6.44 0.65 -0.2253 -7.48 0.55 -0.2262 -8.55 0.44 -0.2252 -9.56 0.34 -0.2206 Tabulated from data in file 07052gw.dat & reduced using program C10.20 Average Reynolds #: 400093.7 Number of angles of attack: 49 alpha / Cl / Cm -10.22 0.31 -0.2332 -9.35 0.39 -0.2344 -8.28 0.50 -0.2386 -7.16 0.61 -0.2381 -6.14 0.70 -0.2379 -5.21 0.78 -0.2352 -4.21 0.87 -0.2358 -3.07 0.97 -0.2317 -2.06 1.05 -0.2295 -1.06 1.14 -0.2256 -0.10 1.21 -0.2210 1.00 1.31 -0.2200 2.03 1.39 -0.2141 3.12 1.47 -0.2080 4.01 1.54 -0.2050 5.17 1.63 -0.1984 6.18 1.71 -0.1950 7.11 1.78 -0.1909 8.19 1.87 -0.1868 9.27 1.94 -0.1811 10.10 1.99 -0.1769 11.21 1.76 -0.1709 12.15 1.66 -0.1815 13.18 1.67 -0.1946 14.05 1.62 -0.2058 13.79 1.64 -0.2023 12.90 1.65 -0.1894 11.90 1.69 -0.1770 11.11 2.02 -0.1708 10.02 1.99 -0.1758 8.84 1.91 -0.1814 7.84 1.85 -0.1865 6.85 1.77 -0.1912 5.97 1.69 -0.1938 4.82 1.61 -0.2012 3.77 1.52 -0.2041 2.84 1.46 -0.2107 1.74 1.36 -0.2130 0.78 1.29 -0.2179 -0.23 1.20 -0.2201 -1.34 1.10 -0.2220 -2.29 1.04 -0.2277 -3.38 0.96 -0.2337 -4.48 0.84 -0.2321 -5.55 0.76 -0.2354 -6.48 0.67 -0.2356 -7.48 0.57 -0.2349 -8.58 0.47 -0.2356 -9.59 0.36 -0.2324 Tabulated from data in file 07051gw.dat & reduced using program C10.20 File w1015-20_fp55_lift.dat created using program clcm dist V1.1 on 30-Mar-2012 09:46:59