Airfoil: GM15 Builder: G. Morris Comment: reflexed (flap = -8.5 degs) Number of Reynolds #'s: 4 Average Reynolds #: 61100 Number of angles of attack: 49 alpha / Cl / Cm -3.50 -0.492 -0.1140 -2.39 -0.377 -0.1140 -1.34 -0.246 -0.1140 -0.50 -0.171 -0.1140 0.66 -0.068 -0.1140 1.64 0.031 -0.1140 2.62 0.132 -0.1140 3.61 0.259 -0.1140 4.64 0.377 -0.1140 5.67 0.480 -0.1140 6.67 0.571 -0.1140 7.70 0.667 -0.1140 8.73 0.763 -0.1140 9.74 0.854 -0.1140 10.80 0.945 -0.1140 11.74 1.013 -0.1140 12.81 1.076 -0.1140 13.87 1.128 -0.1140 14.78 1.147 -0.1140 15.81 1.144 -0.1140 16.77 1.177 -0.1140 17.77 1.111 -0.1140 18.81 1.109 -0.1140 19.86 1.101 -0.1140 20.73 1.077 -0.1140 19.88 1.119 -0.1140 19.01 1.102 -0.1140 17.94 1.129 -0.1140 16.93 1.136 -0.1140 15.94 1.176 -0.1140 14.91 1.156 -0.1140 13.93 1.137 -0.1140 12.93 1.084 -0.1140 11.87 1.016 -0.1140 10.91 0.948 -0.1140 9.85 0.857 -0.1140 8.82 0.761 -0.1140 7.84 0.668 -0.1140 6.74 0.568 -0.1140 5.75 0.477 -0.1140 4.76 0.382 -0.1140 3.73 0.270 -0.1140 2.66 0.126 -0.1140 1.61 0.018 -0.1140 0.64 -0.074 -0.1140 -0.47 -0.182 -0.1140 -1.45 -0.275 -0.1140 -2.60 -0.409 -0.1140 -3.56 -0.500 -0.1140 Tabulated from data in file MS00410.DAT & reduced using program Q01.00L Average Reynolds #: 101800 Number of angles of attack: 33 alpha / Cl / Cm -3.44 -0.514 -0.1140 -1.85 -0.310 -0.1140 -0.18 -0.144 -0.1140 1.29 -0.013 -0.1140 2.65 0.139 -0.1140 4.14 0.286 -0.1140 5.66 0.439 -0.1140 7.31 0.599 -0.1140 8.69 0.733 -0.1140 10.38 0.885 -0.1140 11.80 0.985 -0.1140 13.38 1.077 -0.1140 14.73 1.086 -0.1140 16.35 1.008 -0.1140 17.84 1.003 -0.1140 19.39 0.973 -0.1140 20.76 0.957 -0.1140 19.28 0.984 -0.1140 17.74 1.012 -0.1140 16.28 1.054 -0.1140 14.85 1.119 -0.1140 13.38 1.069 -0.1140 11.83 0.976 -0.1140 10.28 0.864 -0.1140 8.76 0.724 -0.1140 7.23 0.574 -0.1140 5.73 0.427 -0.1140 4.10 0.261 -0.1140 2.59 0.115 -0.1140 1.05 -0.057 -0.1140 -0.63 -0.210 -0.1140 -2.07 -0.367 -0.1140 -3.60 -0.532 -0.1140 Tabulated from data in file JG00406.DAT & reduced using program Q01.00L Average Reynolds #: 203500 Number of angles of attack: 33 alpha / Cl / Cm -3.42 -0.524 -0.1140 -1.82 -0.278 -0.1140 0.02 -0.088 -0.1140 1.54 0.016 -0.1140 3.04 0.163 -0.1140 4.49 0.302 -0.1140 5.96 0.485 -0.1140 7.50 0.645 -0.1140 9.14 0.806 -0.1140 10.61 0.927 -0.1140 12.02 1.030 -0.1140 13.58 1.107 -0.1140 14.73 1.145 -0.1140 16.48 1.151 -0.1140 17.88 1.127 -0.1140 19.66 1.021 -0.1140 20.91 0.980 -0.1140 19.07 1.066 -0.1140 17.46 1.128 -0.1140 16.21 1.152 -0.1140 14.94 1.144 -0.1140 13.23 1.089 -0.1140 11.72 1.007 -0.1140 10.20 0.892 -0.1140 8.65 0.754 -0.1140 7.12 0.597 -0.1140 5.41 0.412 -0.1140 4.00 0.241 -0.1140 2.38 0.084 -0.1140 0.77 -0.059 -0.1140 -0.74 -0.172 -0.1140 -2.40 -0.389 -0.1140 -3.64 -0.557 -0.1140 Tabulated from data in file MS00411.DAT & reduced using program Q01.00L Average Reynolds #: 304300 Number of angles of attack: 33 alpha / Cl / Cm -3.44 -0.517 -0.1140 -1.86 -0.275 -0.1140 -0.32 -0.121 -0.1140 1.95 0.049 -0.1140 2.95 0.157 -0.1140 4.57 0.344 -0.1140 5.99 0.493 -0.1140 7.60 0.658 -0.1140 9.06 0.799 -0.1140 10.57 0.927 -0.1140 12.08 1.042 -0.1140 13.66 1.128 -0.1140 14.52 1.148 -0.1140 16.02 1.161 -0.1140 17.71 1.118 -0.1140 19.24 1.003 -0.1140 20.37 1.034 -0.1140 19.10 0.975 -0.1140 17.79 1.123 -0.1140 16.55 1.168 -0.1140 15.21 1.156 -0.1140 13.21 1.100 -0.1140 11.72 1.011 -0.1140 10.12 0.885 -0.1140 8.45 0.737 -0.1140 7.00 0.589 -0.1140 5.39 0.419 -0.1140 3.94 0.269 -0.1140 2.32 0.078 -0.1140 0.06 -0.095 -0.1140 -0.81 -0.178 -0.1140 -2.29 -0.354 -0.1140 -3.61 -0.549 -0.1140 Tabulated from data in file MS00413.DAT & reduced using program Q01.00L File gm15f1.lft created on 12-05-1997 at 15:25:49 using program FORMAT