Airfoil: AG455ct-02r fp4.6 Builder: M. Drela, et al. Comment: Clean, Flap = 4.6° Number of Reynolds #'s: 5 Average Reynolds #: 100028.0 Number of angles of attack: 49 alpha / Cl / Cm -10.13 -0.49 0.0243 -9.20 -0.44 0.0073 -8.18 -0.40 -0.0164 -7.18 -0.25 -0.0667 -6.26 -0.09 -0.0882 -5.21 0.03 -0.0958 -4.10 0.16 -0.1038 -3.11 0.24 -0.1036 -2.11 0.31 -0.0968 -1.04 0.40 -0.0957 0.01 0.51 -0.1030 1.03 0.65 -0.1143 2.02 0.73 -0.1033 2.99 0.82 -0.0954 4.05 0.90 -0.0906 5.02 0.98 -0.0891 6.08 1.05 -0.0832 7.14 1.11 -0.0786 8.07 1.15 -0.0747 9.10 1.18 -0.0684 10.10 1.15 -0.1488 11.08 1.11 -0.1730 12.05 1.08 -0.1915 12.93 1.05 -0.1870 13.96 1.04 -0.1905 13.77 1.04 -0.1783 12.76 1.07 -0.1823 11.71 1.06 -0.1740 10.76 1.13 -0.1524 9.78 1.19 -0.0907 8.88 1.18 -0.0629 7.88 1.14 -0.0673 6.79 1.09 -0.0731 5.84 1.03 -0.0777 4.83 0.97 -0.0836 3.72 0.87 -0.0876 2.70 0.81 -0.0942 1.64 0.71 -0.0987 0.72 0.60 -0.0984 -0.78 0.45 -0.0872 -1.33 0.38 -0.0857 -2.36 0.30 -0.0910 -3.43 0.22 -0.0960 -4.49 0.11 -0.0929 -5.47 -0.01 -0.0875 -6.47 -0.13 -0.0822 -7.57 -0.32 -0.0352 -8.46 -0.41 0.0033 -9.52 -0.46 0.0211 Tabulated from data in file 06783gw.dat & reduced using program C10.20 Average Reynolds #: 199901.6 Number of angles of attack: 49 alpha / Cl / Cm -10.16 -0.51 0.0300 -9.23 -0.48 0.0073 -8.25 -0.38 -0.0202 -7.25 -0.18 -0.0858 -6.27 -0.04 -0.1020 -5.21 0.08 -0.1067 -4.38 0.14 -0.1084 -3.10 0.25 -0.1126 -2.09 0.35 -0.1128 -1.11 0.45 -0.1133 -0.16 0.56 -0.1115 0.95 0.67 -0.1063 1.99 0.76 -0.1011 3.06 0.85 -0.0959 4.05 0.94 -0.0932 5.06 1.02 -0.0903 6.11 1.10 -0.0854 7.18 1.16 -0.0805 8.14 1.21 -0.0741 9.18 1.24 -0.0682 9.99 1.24 -0.1209 10.95 1.20 -0.1742 11.99 1.14 -0.1915 12.98 1.10 -0.1931 13.98 1.11 -0.1958 13.74 1.12 -0.1945 12.65 1.10 -0.1860 11.71 1.13 -0.1814 10.78 1.19 -0.1651 9.82 1.24 -0.1127 8.82 1.24 -0.0673 7.86 1.21 -0.0736 6.79 1.15 -0.0794 5.88 1.09 -0.0842 4.79 1.01 -0.0883 3.80 0.93 -0.0912 2.71 0.83 -0.0943 1.73 0.75 -0.0992 0.71 0.65 -0.1049 -0.39 0.55 -0.1090 -1.37 0.44 -0.1102 -2.29 0.34 -0.1102 -3.50 0.22 -0.1094 -3.99 0.17 -0.1079 -5.60 0.05 -0.1031 -6.51 -0.06 -0.0979 -7.38 -0.22 -0.0717 -8.54 -0.42 -0.0074 -9.50 -0.48 0.0222 Tabulated from data in file 06785gw.dat & reduced using program C10.20 Average Reynolds #: 299945.0 Number of angles of attack: 45 alpha / Cl / Cm -10.15 -0.51 0.0303 -9.22 -0.47 0.0072 -8.27 -0.34 -0.0438 -7.21 -0.15 -0.0954 -6.12 -0.01 -0.1046 -4.91 0.07 -0.1064 -4.08 0.15 -0.1082 -3.16 0.25 -0.1100 -2.07 0.38 -0.1099 -1.16 0.47 -0.1079 -0.11 0.58 -0.1064 0.91 0.67 -0.1029 1.87 0.76 -0.0985 3.10 0.86 -0.0948 3.99 0.95 -0.0932 5.21 1.05 -0.0890 6.21 1.13 -0.0854 7.13 1.19 -0.0812 8.20 1.24 -0.0744 9.27 1.27 -0.0676 9.99 1.29 -0.1082 11.14 1.25 -0.1590 11.99 1.19 -0.1820 11.73 1.19 -0.1792 10.76 1.25 -0.1462 9.78 1.27 -0.0817 8.85 1.26 -0.0695 7.93 1.24 -0.0755 6.71 1.16 -0.0825 5.87 1.10 -0.0862 4.91 1.02 -0.0897 3.69 0.93 -0.0930 2.62 0.83 -0.0945 1.72 0.75 -0.0978 0.58 0.64 -0.1017 -0.45 0.54 -0.1050 -1.36 0.45 -0.1069 -2.35 0.34 -0.1084 -3.49 0.22 -0.1083 -4.54 0.11 -0.1064 -5.27 0.07 -0.1054 -6.46 -0.04 -0.1024 -7.50 -0.20 -0.0836 -8.51 -0.39 -0.0238 -9.51 -0.49 0.0170 Tabulated from data in file 06787gw.dat & reduced using program C10.20 Average Reynolds #: 399460.7 Number of angles of attack: 33 alpha / Cl / Cm -7.21 -0.12 -0.0986 -6.18 -0.01 -0.1030 -5.28 0.04 -0.1038 -4.16 0.15 -0.1058 -3.12 0.27 -0.1064 -2.05 0.38 -0.1064 -1.04 0.49 -0.1046 0.04 0.59 -0.1020 0.93 0.68 -0.0997 2.06 0.78 -0.0965 3.14 0.88 -0.0951 4.07 0.96 -0.0925 5.07 1.05 -0.0896 6.06 1.13 -0.0861 7.10 1.21 -0.0815 8.08 1.26 -0.0756 9.25 1.29 -0.0686 8.82 1.29 -0.0710 7.83 1.24 -0.0772 6.71 1.18 -0.0831 5.68 1.10 -0.0876 4.83 1.03 -0.0904 3.82 0.93 -0.0925 2.66 0.84 -0.0949 1.70 0.75 -0.0971 0.64 0.64 -0.0995 -0.45 0.54 -0.1022 -1.46 0.44 -0.1045 -2.41 0.34 -0.1061 -3.50 0.23 -0.1052 -4.53 0.11 -0.1036 -4.96 0.07 -0.1030 -6.55 -0.04 -0.1016 Tabulated from data in file 06789ga.dat & reduced using program C10.20 Average Reynolds #: 500321.8 Number of angles of attack: 33 alpha / Cl / Cm -7.22 -0.11 -0.0984 -6.24 -0.01 -0.1012 -5.10 0.06 -0.1025 -4.13 0.17 -0.1027 -3.06 0.28 -0.1043 -2.02 0.39 -0.1037 -1.03 0.49 -0.1027 -0.10 0.58 -0.1006 1.03 0.68 -0.0969 2.09 0.78 -0.0951 3.06 0.88 -0.0933 4.15 0.97 -0.0908 5.22 1.07 -0.0884 6.15 1.14 -0.0845 7.27 1.22 -0.0801 8.16 1.27 -0.0758 9.24 1.31 -0.0702 8.74 1.30 -0.0720 7.66 1.25 -0.0778 6.69 1.19 -0.0830 5.63 1.10 -0.0862 4.79 1.03 -0.0888 3.75 0.94 -0.0917 2.55 0.83 -0.0939 1.62 0.74 -0.0953 0.72 0.65 -0.0974 -0.39 0.55 -0.1007 -1.59 0.44 -0.1030 -2.54 0.34 -0.1042 -3.56 0.23 -0.1034 -4.48 0.13 -0.1025 -5.06 0.06 -0.1010 -6.54 -0.04 -0.1004 Tabulated from data in file 06791ga.dat & reduced using program C10.20 File ag455ct_fp5_lift.dat created using program clcm dist V1.1 on 30-Mar-2012 09:46:56