Airfoil: MA409 Builder: R. Cooney Comment: gurney flap (h/c = 0.4%) Number of Reynolds #'s: 4 Average Reynolds #: 60200 Number of angles of attack: 49 alpha / Cl / Cm -6.37 -0.373 -0.1150 -4.52 -0.241 -0.1150 -3.76 -0.187 -0.1150 -2.72 -0.106 -0.1150 -1.61 -0.014 -0.1150 -0.58 0.093 -0.1150 0.55 0.204 -0.1150 1.42 0.300 -0.1150 2.45 0.461 -0.1150 3.44 0.574 -0.1150 4.44 0.655 -0.1150 5.47 0.756 -0.1150 6.50 0.818 -0.1150 7.57 0.884 -0.1150 8.60 0.946 -0.1150 9.69 0.998 -0.1150 10.66 1.020 -0.1150 11.67 1.031 -0.1150 12.67 1.002 -0.1150 13.53 0.999 -0.1150 14.52 1.007 -0.1150 15.81 0.963 -0.1150 16.53 0.985 -0.1150 17.57 0.978 -0.1150 18.67 0.952 -0.1150 16.79 1.011 -0.1150 16.08 1.034 -0.1150 14.93 1.069 -0.1150 14.03 1.035 -0.1150 12.86 1.076 -0.1150 11.91 1.097 -0.1150 10.92 1.110 -0.1150 9.93 1.109 -0.1150 9.10 1.078 -0.1150 7.88 1.016 -0.1150 6.87 0.956 -0.1150 5.87 0.887 -0.1150 4.88 0.788 -0.1150 3.87 0.697 -0.1150 2.93 0.610 -0.1150 1.70 0.435 -0.1150 0.77 0.341 -0.1150 -0.12 0.249 -0.1150 -1.28 0.139 -0.1150 -2.36 0.049 -0.1150 -3.23 -0.024 -0.1150 -4.47 -0.122 -0.1150 -5.34 -0.203 -0.1150 -6.28 -0.317 -0.1150 Tabulated from data in file CL00920.DAT & reduced using program Q02.00L Average Reynolds #: 100400 Number of angles of attack: 49 alpha / Cl / Cm -5.81 -0.359 -0.1150 -4.80 -0.232 -0.1150 -3.73 -0.133 -0.1150 -2.66 -0.038 -0.1150 -1.66 0.063 -0.1150 -0.62 0.149 -0.1150 0.42 0.259 -0.1150 1.44 0.402 -0.1150 2.46 0.541 -0.1150 3.65 0.656 -0.1150 4.57 0.737 -0.1150 5.61 0.828 -0.1150 6.67 0.911 -0.1150 7.74 0.979 -0.1150 8.47 1.024 -0.1150 9.58 1.081 -0.1150 10.59 1.099 -0.1150 11.73 1.091 -0.1150 12.69 1.050 -0.1150 13.65 1.019 -0.1150 14.65 0.989 -0.1150 15.69 1.014 -0.1150 16.78 0.974 -0.1150 17.74 0.996 -0.1150 18.52 0.990 -0.1150 16.82 1.012 -0.1150 15.81 1.011 -0.1150 14.83 1.050 -0.1150 13.99 1.039 -0.1150 13.06 1.053 -0.1150 11.84 1.096 -0.1150 11.15 1.119 -0.1150 10.10 1.108 -0.1150 9.06 1.059 -0.1150 7.81 0.996 -0.1150 7.05 0.944 -0.1150 5.78 0.847 -0.1150 5.06 0.789 -0.1150 3.79 0.670 -0.1150 2.82 0.578 -0.1150 1.89 0.471 -0.1150 0.66 0.293 -0.1150 -0.29 0.198 -0.1150 -1.25 0.104 -0.1150 -2.19 0.026 -0.1150 -3.48 -0.093 -0.1150 -4.49 -0.184 -0.1150 -5.52 -0.281 -0.1150 -6.36 -0.412 -0.1150 Tabulated from data in file CL00922.DAT & reduced using program Q02.00L Average Reynolds #: 200600 Number of angles of attack: 49 alpha / Cl / Cm -6.10 -0.346 -0.1150 -4.48 -0.156 -0.1150 -3.71 -0.082 -0.1150 -2.46 0.039 -0.1150 -1.60 0.129 -0.1150 -0.53 0.243 -0.1150 0.61 0.354 -0.1150 1.46 0.447 -0.1150 2.46 0.551 -0.1150 3.53 0.656 -0.1150 4.48 0.751 -0.1150 5.57 0.850 -0.1150 6.66 0.940 -0.1150 7.73 1.015 -0.1150 8.77 1.079 -0.1150 9.70 1.130 -0.1150 10.63 1.158 -0.1150 11.74 1.151 -0.1150 12.57 1.155 -0.1150 13.66 1.102 -0.1150 14.52 1.082 -0.1150 15.49 1.074 -0.1150 16.80 1.047 -0.1150 17.65 1.044 -0.1150 18.66 1.009 -0.1150 16.81 1.021 -0.1150 15.89 1.065 -0.1150 15.10 1.077 -0.1150 13.87 1.111 -0.1150 13.13 1.146 -0.1150 11.79 1.154 -0.1150 10.98 1.168 -0.1150 9.73 1.127 -0.1150 9.11 1.093 -0.1150 7.80 1.021 -0.1150 7.10 0.974 -0.1150 5.76 0.864 -0.1150 5.08 0.802 -0.1150 3.69 0.665 -0.1150 3.02 0.599 -0.1150 1.62 0.460 -0.1150 0.92 0.384 -0.1150 -0.17 0.280 -0.1150 -1.21 0.166 -0.1150 -2.46 0.035 -0.1150 -3.36 -0.052 -0.1150 -4.18 -0.131 -0.1150 -5.27 -0.235 -0.1150 -6.28 -0.384 -0.1150 Tabulated from data in file CL00924.DAT & reduced using program Q02.00L Average Reynolds #: 300600 Number of angles of attack: 49 alpha / Cl / Cm -6.23 -0.330 -0.1150 -4.69 -0.153 -0.1150 -3.85 -0.069 -0.1150 -2.74 0.045 -0.1150 -1.59 0.169 -0.1150 -0.63 0.292 -0.1150 0.32 0.350 -0.1150 1.36 0.451 -0.1150 2.57 0.574 -0.1150 3.67 0.687 -0.1150 4.50 0.768 -0.1150 5.64 0.876 -0.1150 6.81 0.978 -0.1150 7.70 1.040 -0.1150 8.91 1.114 -0.1150 9.75 1.160 -0.1150 10.60 1.171 -0.1150 11.62 1.179 -0.1150 12.41 1.157 -0.1150 13.24 1.112 -0.1150 14.40 1.021 -0.1150 15.28 1.012 -0.1150 16.35 1.022 -0.1150 17.33 1.016 -0.1150 18.39 1.023 -0.1150 17.08 1.028 -0.1150 16.11 1.025 -0.1150 15.14 1.007 -0.1150 14.17 1.022 -0.1150 13.14 1.068 -0.1150 11.98 1.174 -0.1150 11.17 1.168 -0.1150 9.83 1.148 -0.1150 8.99 1.108 -0.1150 7.84 1.039 -0.1150 6.89 0.973 -0.1150 5.74 0.878 -0.1150 4.89 0.798 -0.1150 3.70 0.686 -0.1150 2.86 0.602 -0.1150 1.73 0.484 -0.1150 0.88 0.399 -0.1150 -0.35 0.320 -0.1150 -1.34 0.195 -0.1150 -2.21 0.102 -0.1150 -3.25 -0.008 -0.1150 -4.48 -0.131 -0.1150 -5.50 -0.233 -0.1150 -6.39 -0.358 -0.1150 Tabulated from data in file CL00926.DAT & reduced using program Q02.00L File ma409gf4.lft created on 09-12-1997 at 13:46:18 using program FORMAT