Airfoil: W1011-30 fp60 Builder: S. Cassidy Comment: Clean, Cf/C = 30%, Flap = 60° Number of Reynolds #'s: 3 Average Reynolds #: 100051.0 Number of angles of attack: 33 alpha / Cl / Cm -10.27 0.57 -0.1930 -9.17 0.68 -0.2032 -8.06 0.79 -0.2081 -7.02 0.89 -0.2107 -6.14 0.97 -0.2130 -5.06 1.05 -0.2129 -3.95 1.16 -0.2146 -3.06 1.26 -0.2240 -1.96 1.33 -0.2147 -1.00 1.38 -0.2120 0.11 1.45 -0.2077 1.03 1.52 -0.2052 2.04 1.58 -0.2001 3.17 1.63 -0.1949 4.06 1.48 -0.2342 5.03 1.43 -0.2623 5.91 1.37 -0.2729 5.69 1.37 -0.2575 4.83 1.44 -0.2405 3.92 1.61 -0.1878 2.87 1.62 -0.1819 1.83 1.57 -0.1884 0.93 1.51 -0.1909 -0.16 1.44 -0.1933 -1.25 1.37 -0.1965 -2.23 1.32 -0.2024 -3.21 1.23 -0.2005 -4.34 1.14 -0.2005 -5.34 1.03 -0.1971 -6.44 0.95 -0.1943 -7.30 0.87 -0.1924 -8.27 0.77 -0.1885 -9.38 0.67 -0.1835 Tabulated from data in file 07182gw.dat & reduced using program C10.20 Average Reynolds #: 199976.7 Number of angles of attack: 33 alpha / Cl / Cm -10.22 0.67 -0.2166 -9.08 0.77 -0.2212 -8.11 0.85 -0.2226 -7.17 0.92 -0.2238 -6.08 1.00 -0.2197 -5.09 1.09 -0.2224 -4.01 1.19 -0.2226 -3.09 1.24 -0.2172 -1.96 1.33 -0.2163 -1.00 1.38 -0.2084 0.06 1.46 -0.2063 1.00 1.52 -0.2049 2.17 1.59 -0.2019 3.07 1.65 -0.2013 4.08 1.72 -0.1968 5.13 1.55 -0.2602 6.01 1.44 -0.2753 5.66 1.44 -0.2649 4.80 1.58 -0.2466 3.95 1.70 -0.1909 2.90 1.63 -0.1914 1.81 1.57 -0.1991 0.71 1.49 -0.1956 -0.22 1.44 -0.2022 -1.18 1.38 -0.2069 -2.18 1.30 -0.2050 -3.16 1.25 -0.2119 -4.38 1.16 -0.2164 -5.24 1.07 -0.2135 -6.38 0.97 -0.2120 -7.33 0.90 -0.2143 -8.42 0.82 -0.2153 -9.37 0.74 -0.2125 Tabulated from data in file 07183gw.dat & reduced using program C10.20 Average Reynolds #: 399808.1 Number of angles of attack: 31 alpha / Cl / Cm -10.21 0.81 -0.2680 -9.26 0.87 -0.2657 -8.18 0.95 -0.2621 -7.06 1.04 -0.2601 -6.07 1.10 -0.2554 -5.08 1.18 -0.2510 -3.95 1.22 -0.2398 -2.99 1.28 -0.2317 -2.08 1.34 -0.2296 -0.90 1.42 -0.2248 0.03 1.48 -0.2185 1.09 1.57 -0.2172 2.12 1.63 -0.2115 3.16 1.70 -0.2060 4.16 1.76 -0.2001 5.01 1.80 -0.1950 4.82 1.79 -0.1943 3.80 1.74 -0.2011 2.88 1.68 -0.2065 1.92 1.61 -0.2086 0.70 1.54 -0.2159 -0.17 1.47 -0.2171 -1.25 1.40 -0.2247 -2.36 1.33 -0.2287 -3.25 1.27 -0.2329 -4.44 1.21 -0.2467 -5.37 1.14 -0.2467 -6.49 1.07 -0.2535 -7.44 1.00 -0.2571 -8.36 0.95 -0.2624 -9.55 0.85 -0.2627 Tabulated from data in file 07184gw.dat & reduced using program C10.20 File w1011-30_fp60_lift.dat created using program clcm dist V1.1 on 30-Mar-2012 09:46:58