Airfoil: W1015-20 fp60 Builder: S. Cassidy Comment: Clean, Cf/C = 20%, Flap = 60° Number of Reynolds #'s: 3 Average Reynolds #: 100032.6 Number of angles of attack: 47 alpha / Cl / Cm -10.24 -0.09 -0.0988 -9.13 0.04 -0.1115 -8.10 0.19 -0.1262 -7.14 0.28 -0.1274 -6.16 0.39 -0.1348 -5.09 0.53 -0.1472 -3.98 0.65 -0.1529 -3.02 0.77 -0.1642 -1.95 0.91 -0.1737 -1.02 1.03 -0.1888 0.05 1.15 -0.1925 1.11 1.23 -0.1894 2.00 1.30 -0.1879 3.12 1.38 -0.1848 4.19 1.46 -0.1814 5.23 1.53 -0.1784 6.13 1.60 -0.1750 7.21 1.68 -0.1751 8.21 1.73 -0.1700 9.30 1.77 -0.1645 10.22 1.79 -0.1606 10.93 1.26 -0.2732 11.88 1.30 -0.2821 12.96 1.38 -0.2950 12.77 1.37 -0.2772 11.67 1.35 -0.2709 10.83 1.29 -0.2577 9.74 1.29 -0.2527 8.61 1.25 -0.2407 7.63 1.25 -0.2252 6.90 1.67 -0.1597 5.81 1.61 -0.1612 4.74 1.52 -0.1627 3.71 1.44 -0.1633 2.72 1.37 -0.1640 1.91 1.30 -0.1652 0.67 1.20 -0.1650 -0.15 1.14 -0.1688 -1.39 0.98 -0.1588 -2.28 0.86 -0.1482 -3.37 0.74 -0.1421 -4.46 0.61 -0.1320 -5.49 0.49 -0.1254 -6.23 0.40 -0.1173 -7.47 0.26 -0.1064 -8.42 0.17 -0.1024 -9.50 0.00 -0.0782 Tabulated from data in file 07048gw.dat & reduced using program C10.20 Average Reynolds #: 200108.0 Number of angles of attack: 49 alpha / Cl / Cm -10.20 0.35 -0.2302 -9.17 0.45 -0.2335 -8.26 0.54 -0.2345 -7.11 0.63 -0.2320 -6.19 0.73 -0.2340 -5.12 0.79 -0.2267 -4.08 0.87 -0.2192 -3.14 0.93 -0.2108 -2.07 1.00 -0.2034 -1.02 1.08 -0.1988 0.01 1.15 -0.1905 1.00 1.22 -0.1883 2.06 1.32 -0.1895 3.14 1.41 -0.1868 4.17 1.50 -0.1874 5.10 1.56 -0.1845 6.17 1.66 -0.1824 7.12 1.71 -0.1785 8.13 1.78 -0.1762 9.30 1.85 -0.1712 10.24 1.91 -0.1709 11.25 1.73 -0.1582 12.23 1.67 -0.1675 12.81 1.37 -0.2946 13.85 1.36 -0.2997 13.74 1.36 -0.2955 12.65 1.37 -0.2872 11.68 1.36 -0.2818 10.68 1.30 -0.2690 9.75 1.32 -0.2620 8.89 1.84 -0.1709 7.82 1.77 -0.1718 6.82 1.70 -0.1745 5.76 1.63 -0.1788 4.83 1.54 -0.1792 3.84 1.47 -0.1814 2.73 1.38 -0.1839 1.73 1.30 -0.1836 0.81 1.22 -0.1858 -0.30 1.13 -0.1880 -1.32 1.07 -0.1950 -2.35 0.99 -0.2007 -3.28 0.92 -0.2048 -4.39 0.85 -0.2148 -5.46 0.77 -0.2212 -6.46 0.70 -0.2261 -7.42 0.61 -0.2262 -8.40 0.52 -0.2265 -9.54 0.41 -0.2256 Tabulated from data in file 07049gw.dat & reduced using program C10.20 Average Reynolds #: 400265.9 Number of angles of attack: 47 alpha / Cl / Cm -10.35 0.35 -0.2361 -9.20 0.47 -0.2381 -8.28 0.55 -0.2402 -7.18 0.65 -0.2402 -6.17 0.73 -0.2362 -5.12 0.83 -0.2370 -4.06 0.93 -0.2360 -3.06 1.02 -0.2346 -2.08 1.09 -0.2299 -1.11 1.16 -0.2247 -0.02 1.26 -0.2219 1.10 1.34 -0.2182 2.04 1.42 -0.2135 3.06 1.50 -0.2082 4.10 1.58 -0.2031 5.04 1.63 -0.1975 6.16 1.73 -0.1931 7.19 1.81 -0.1888 8.15 1.88 -0.1851 9.19 1.96 -0.1817 10.19 2.01 -0.1764 11.19 1.73 -0.1713 11.99 1.67 -0.1788 13.07 1.67 -0.1936 12.84 1.67 -0.1886 11.96 1.69 -0.1777 10.98 2.05 -0.1729 9.87 2.00 -0.1778 8.84 1.93 -0.1828 7.87 1.87 -0.1862 6.86 1.80 -0.1915 5.90 1.72 -0.1953 4.90 1.64 -0.1991 3.75 1.55 -0.2037 2.92 1.49 -0.2075 1.71 1.40 -0.2129 0.72 1.32 -0.2173 -0.26 1.24 -0.2212 -1.27 1.16 -0.2234 -2.31 1.07 -0.2276 -3.42 0.98 -0.2327 -4.40 0.89 -0.2328 -5.48 0.80 -0.2358 -6.38 0.72 -0.2360 -7.50 0.63 -0.2373 -8.54 0.51 -0.2342 -9.58 0.43 -0.2367 Tabulated from data in file 07050gw.dat & reduced using program C10.20 File w1015-20_fp60_lift.dat created using program clcm dist V1.1 on 30-Mar-2012 09:46:59