Airfoil: S7012 (B) Builder: M. Lachowski Comment: clean: flap = 5 degs Number of Reynolds #'s: 4 Average Reynolds #: 60500 Number of angles of attack: 49 alpha / Cl / Cm -6.05 -0.267 -0.1000 -4.61 -0.125 -0.1000 -3.60 -0.032 -0.1000 -2.57 0.047 -0.1000 -1.54 0.135 -0.1000 -0.52 0.245 -0.1000 0.51 0.355 -0.1000 1.60 0.532 -0.1000 2.66 0.686 -0.1000 3.70 0.799 -0.1000 4.73 0.885 -0.1000 5.78 0.970 -0.1000 6.65 1.035 -0.1000 7.71 1.090 -0.1000 8.76 1.136 -0.1000 9.80 1.163 -0.1000 10.78 1.131 -0.1000 11.76 1.125 -0.1000 12.72 1.096 -0.1000 13.67 1.025 -0.1000 14.66 1.040 -0.1000 15.75 1.040 -0.1000 16.79 1.005 -0.1000 17.62 0.980 -0.1000 18.64 0.997 -0.1000 17.17 1.219 -0.1000 16.33 1.192 -0.1000 15.25 1.146 -0.1000 14.21 1.117 -0.1000 13.22 1.095 -0.1000 12.23 1.035 -0.1000 11.30 1.136 -0.1000 10.15 1.144 -0.1000 9.37 1.126 -0.1000 8.34 1.098 -0.1000 7.35 1.046 -0.1000 6.29 0.986 -0.1000 5.16 0.895 -0.1000 4.09 0.808 -0.1000 3.26 0.733 -0.1000 2.22 0.608 -0.1000 1.17 0.430 -0.1000 0.14 0.276 -0.1000 -1.02 0.152 -0.1000 -2.03 0.048 -0.1000 -3.02 -0.030 -0.1000 -4.01 -0.111 -0.1000 -5.05 -0.206 -0.1000 -6.08 -0.297 -0.1000 Tabulated from data in file CL00855.DAT & reduced using program Q02.00L Average Reynolds #: 100300 Number of angles of attack: 49 alpha / Cl / Cm -6.03 -0.225 -0.1000 -4.57 -0.084 -0.1000 -3.47 0.002 -0.1000 -2.63 0.049 -0.1000 -1.38 0.167 -0.1000 -0.54 0.256 -0.1000 0.59 0.460 -0.1000 1.58 0.594 -0.1000 2.68 0.714 -0.1000 3.63 0.798 -0.1000 4.72 0.896 -0.1000 5.83 0.999 -0.1000 6.70 1.061 -0.1000 7.82 1.109 -0.1000 8.65 1.143 -0.1000 9.78 1.175 -0.1000 10.72 1.195 -0.1000 11.77 1.157 -0.1000 12.83 1.133 -0.1000 13.64 1.048 -0.1000 14.87 1.045 -0.1000 15.75 1.064 -0.1000 16.86 1.017 -0.1000 17.64 1.018 -0.1000 18.86 1.036 -0.1000 17.04 1.036 -0.1000 16.21 1.048 -0.1000 15.24 1.039 -0.1000 14.26 1.054 -0.1000 13.32 1.052 -0.1000 12.20 1.115 -0.1000 11.24 1.184 -0.1000 10.12 1.180 -0.1000 9.15 1.150 -0.1000 8.25 1.118 -0.1000 7.14 1.070 -0.1000 6.26 1.022 -0.1000 5.11 0.920 -0.1000 4.21 0.839 -0.1000 3.10 0.738 -0.1000 1.97 0.626 -0.1000 1.09 0.525 -0.1000 -0.04 0.339 -0.1000 -0.92 0.206 -0.1000 -2.02 0.087 -0.1000 -3.13 0.002 -0.1000 -3.97 -0.049 -0.1000 -5.12 -0.137 -0.1000 -6.02 -0.208 -0.1000 Tabulated from data in file CL00857.DAT & reduced using program Q02.00L Average Reynolds #: 200500 Number of angles of attack: 49 alpha / Cl / Cm -5.54 -0.097 -0.1000 -4.52 0.002 -0.1000 -3.49 0.104 -0.1000 -2.48 0.202 -0.1000 -1.49 0.286 -0.1000 -0.20 0.422 -0.1000 0.76 0.508 -0.1000 1.72 0.607 -0.1000 2.68 0.701 -0.1000 3.60 0.814 -0.1000 4.82 0.933 -0.1000 5.80 1.017 -0.1000 6.77 1.076 -0.1000 7.71 1.127 -0.1000 8.89 1.171 -0.1000 9.81 1.188 -0.1000 10.76 1.208 -0.1000 11.68 1.195 -0.1000 12.74 1.143 -0.1000 13.66 1.096 -0.1000 14.69 1.064 -0.1000 15.81 1.056 -0.1000 16.69 1.029 -0.1000 17.72 1.028 -0.1000 18.88 1.031 -0.1000 17.09 1.019 -0.1000 16.13 1.054 -0.1000 15.10 1.065 -0.1000 14.11 1.088 -0.1000 13.02 1.137 -0.1000 12.33 1.186 -0.1000 11.13 1.196 -0.1000 10.14 1.186 -0.1000 9.37 1.173 -0.1000 8.11 1.135 -0.1000 7.13 1.083 -0.1000 6.24 1.034 -0.1000 5.03 0.938 -0.1000 4.23 0.861 -0.1000 2.98 0.735 -0.1000 2.13 0.632 -0.1000 1.03 0.523 -0.1000 -0.10 0.420 -0.1000 -1.07 0.311 -0.1000 -2.03 0.232 -0.1000 -3.24 0.112 -0.1000 -4.17 0.020 -0.1000 -5.09 -0.070 -0.1000 -6.25 -0.185 -0.1000 Tabulated from data in file CL00859.DAT & reduced using program Q02.00L Average Reynolds #: 300800 Number of angles of attack: 49 alpha / Cl / Cm -6.04 -0.168 -0.1000 -4.30 0.007 -0.1000 -3.53 0.086 -0.1000 -2.40 0.192 -0.1000 -1.40 0.301 -0.1000 -0.44 0.412 -0.1000 0.61 0.515 -0.1000 1.67 0.616 -0.1000 2.78 0.732 -0.1000 3.59 0.815 -0.1000 4.76 0.929 -0.1000 5.85 1.018 -0.1000 6.93 1.093 -0.1000 7.72 1.140 -0.1000 8.82 1.183 -0.1000 9.69 1.201 -0.1000 10.79 1.240 -0.1000 11.82 1.237 -0.1000 12.63 1.218 -0.1000 13.73 1.169 -0.1000 14.59 1.106 -0.1000 15.60 1.051 -0.1000 16.56 1.029 -0.1000 17.60 1.000 -0.1000 18.56 1.039 -0.1000 17.21 1.016 -0.1000 16.16 1.038 -0.1000 15.21 1.067 -0.1000 14.19 1.131 -0.1000 13.19 1.192 -0.1000 12.24 1.208 -0.1000 11.32 1.229 -0.1000 10.16 1.206 -0.1000 9.04 1.183 -0.1000 8.25 1.158 -0.1000 7.08 1.096 -0.1000 6.17 1.035 -0.1000 5.23 0.964 -0.1000 4.20 0.872 -0.1000 3.13 0.764 -0.1000 2.07 0.653 -0.1000 0.93 0.540 -0.1000 -0.21 0.431 -0.1000 -1.01 0.356 -0.1000 -2.20 0.209 -0.1000 -3.10 0.126 -0.1000 -4.22 0.014 -0.1000 -5.26 -0.089 -0.1000 -6.37 -0.198 -0.1000 Tabulated from data in file CL00861.DAT & reduced using program Q02.00L File s7012bf5.lft created on 09-12-1997 at 13:46:18 using program FORMAT