Airfoil: W1011-30 fp10 Builder: S. Cassidy Comment: Clean, Cf/C = 30%, Flap = 10° Number of Reynolds #'s: 3 Average Reynolds #: 99983.3 Number of angles of attack: 45 alpha / Cl / Cm -10.19 -0.35 -0.1075 -9.20 -0.26 -0.1114 -8.31 -0.17 -0.1141 -7.15 -0.06 -0.1149 -6.17 0.02 -0.1142 -5.16 0.11 -0.1138 -4.20 0.19 -0.1150 -3.05 0.30 -0.1070 -2.19 0.38 -0.1142 -1.16 0.44 -0.1018 -0.15 0.51 -0.0983 0.90 0.71 -0.1145 1.98 0.78 -0.0950 2.98 0.87 -0.0913 4.09 0.94 -0.0873 5.15 1.01 -0.0822 6.19 1.06 -0.0769 7.19 1.11 -0.0714 8.10 1.15 -0.0668 9.02 1.03 -0.1597 9.96 0.96 -0.1702 11.01 0.96 -0.1760 12.02 0.95 -0.1773 11.82 0.96 -0.1614 10.73 0.95 -0.1552 9.69 0.98 -0.1491 8.84 1.21 -0.0566 7.80 1.17 -0.0619 6.84 1.12 -0.0667 5.80 1.06 -0.0729 4.70 1.01 -0.0790 3.83 0.94 -0.0832 2.73 0.85 -0.0876 1.83 0.78 -0.0915 0.71 0.67 -0.0978 -0.41 0.50 -0.0912 -1.31 0.44 -0.0890 -2.30 0.38 -0.0935 -3.32 0.28 -0.0979 -4.30 0.19 -0.0967 -5.51 0.09 -0.1030 -6.43 0.02 -0.1034 -7.49 -0.08 -0.1083 -8.51 -0.18 -0.1090 -9.54 -0.27 -0.1089 Tabulated from data in file 07139gw.dat & reduced using program C10.20 Average Reynolds #: 200087.8 Number of angles of attack: 49 alpha / Cl / Cm -10.20 -0.38 -0.1028 -9.24 -0.28 -0.1043 -8.21 -0.19 -0.1058 -7.14 -0.08 -0.1076 -6.11 0.02 -0.1084 -5.24 0.11 -0.1094 -4.10 0.22 -0.1091 -3.24 0.30 -0.1081 -2.15 0.41 -0.1086 -1.04 0.52 -0.1104 -0.10 0.62 -0.1097 0.84 0.71 -0.1021 2.09 0.81 -0.0973 3.08 0.89 -0.0940 4.12 0.97 -0.0905 5.15 1.04 -0.0861 6.11 1.09 -0.0811 7.11 1.15 -0.0755 8.19 1.20 -0.0696 9.19 1.24 -0.0643 9.89 1.06 -0.1669 10.97 0.98 -0.1739 11.90 0.99 -0.1796 12.95 0.95 -0.1796 13.89 0.92 -0.1778 13.61 0.93 -0.1723 12.66 0.96 -0.1721 11.67 1.00 -0.1740 10.80 1.01 -0.1712 9.69 1.05 -0.1579 8.86 1.22 -0.0602 7.87 1.19 -0.0654 6.91 1.14 -0.0715 5.87 1.08 -0.0771 4.85 1.03 -0.0829 3.79 0.95 -0.0878 2.80 0.87 -0.0912 1.84 0.79 -0.0940 0.76 0.71 -0.0994 -0.42 0.60 -0.1072 -1.45 0.49 -0.1063 -2.44 0.39 -0.1065 -3.48 0.28 -0.1078 -4.50 0.18 -0.1077 -5.47 0.09 -0.1083 -6.40 -0.01 -0.1073 -7.59 -0.12 -0.1064 -8.60 -0.22 -0.1055 -9.49 -0.31 -0.1045 Tabulated from data in file 07141gw.dat & reduced using program C10.20 Average Reynolds #: 399714.0 Number of angles of attack: 43 alpha / Cl / Cm -10.49 -0.43 -0.1006 -9.21 -0.31 -0.1026 -8.32 -0.21 -0.1035 -7.27 -0.10 -0.1046 -6.30 0.00 -0.1058 -5.23 0.11 -0.1061 -4.26 0.21 -0.1071 -3.26 0.32 -0.1083 -2.13 0.42 -0.1084 -1.07 0.53 -0.1090 0.00 0.63 -0.1037 1.00 0.71 -0.1000 2.00 0.81 -0.0981 3.06 0.89 -0.0951 4.10 0.98 -0.0918 5.05 1.06 -0.0892 6.13 1.13 -0.0834 7.12 1.19 -0.0785 8.04 1.23 -0.0728 9.06 1.27 -0.0667 10.15 1.32 -0.0616 11.20 1.33 -0.0581 10.83 1.33 -0.0577 9.82 1.31 -0.0617 8.82 1.27 -0.0667 7.95 1.23 -0.0719 6.79 1.16 -0.0782 5.90 1.12 -0.0833 4.74 1.03 -0.0880 3.83 0.96 -0.0910 2.71 0.87 -0.0945 1.69 0.77 -0.0968 0.75 0.69 -0.1000 -0.29 0.61 -0.1053 -1.37 0.51 -0.1082 -2.50 0.39 -0.1077 -3.37 0.31 -0.1073 -4.38 0.21 -0.1065 -5.51 0.08 -0.1050 -6.46 -0.01 -0.1045 -7.40 -0.11 -0.1040 -8.39 -0.22 -0.1029 -9.54 -0.34 -0.1016 Tabulated from data in file 07143gw.dat & reduced using program C10.20 File w1011-30_fp10_lift.dat created using program clcm dist V1.1 on 30-Mar-2012 09:46:58